Cloud diffusion enhancement device and high-altitude simulated icing test stand for aircraft engine icing tests

Abstract

This invention discloses a cloud and fog diffusion enhancement device for aero-engine icing tests and a high-altitude simulated icing test stand, comprising: a spray device and several diffusion enhancement vortex generators. The spray device includes several atomizing nozzles facing the inlet of the test engine. Several diffusion enhancement vortex generators are correspondingly mounted on the spray ends of the atomizing nozzles. Each diffusion enhancement vortex generator has several through-holes for airflow penetration. The diffusion enhancement vortex generators allow the incoming high-speed main airflow to pass through the airflow penetrations and form a low-speed vortex zone on the back side of the diffusion enhancement vortex generator. This, in turn, causes the cloud and fog particles ejected from the corresponding atomizing nozzles to flow back with the vortex and diffuse outwards towards the edge of the diffusion enhancement vortex generator, merging with the high-speed main airflow before being sprayed towards the test engine. This invention's device has strong applicability and can enhance the diffusion of cloud and fog particles ejected from the atomizing nozzles, thereby improving the uniformity of cloud and fog particles at the engine inlet during aero-engine icing tests.

Description

Technical Field

[0001] This invention relates to the technical field of aircraft engine icing test equipment, and in particular, to a cloud diffusion enhancement device for aircraft engine icing tests. Furthermore, this invention also relates to a high-altitude simulated icing test stand incorporating the aforementioned cloud diffusion enhancement device for aircraft engine icing tests. Background Technology

[0002] Aircraft engines may experience internal icing under icing weather conditions, which can seriously affect flight safety. To avoid flight accidents caused by icing, ground-based icing verification tests of aircraft engines must be completed in accordance with airworthiness regulations. Currently, the optimal method for constructing an icing cloud environment that complies with airworthiness regulations is to install a spray device in a high-altitude simulated icing test stand. Water is atomized into cloud particles through multiple nozzles of the spray device and mixed in a specific ratio with high-speed cold air intake from the high-altitude simulation chamber to form an icing cloud environment. This mixture is then sprayed at high speed towards the test engine and ingested, keeping the engine constantly in an icing environment to assess the aircraft engine's anti-icing capability.

[0003] The challenge of ground icing verification tests for aero-engines lies in how to construct an icing cloud and fog environment that complies with airworthiness regulations to ensure the rationality, effectiveness, and accuracy of the icing test. In constructing the icing cloud and fog environment, the uniformity of the cloud and fog is particularly critical. Poor cloud and fog uniformity cannot simulate the real cloud and fog environment, thereby reducing the accuracy of the aero-engine icing verification test.

[0004] Currently, domestic and international spraying devices adopt the following... Figure 2 The supported spray layout shown allows for sufficient diffusion of cloud particles ejected from the nozzles under windless or extremely low flow conditions, resulting in acceptable uniformity of the cloud particles. However, in the actual icing environment of an aero-engine, various flight conditions need to be simulated. When the flow rate increases, the cloud particles ejected from the nozzles are prone to clustering as they flow toward the engine, making diffusion difficult and significantly reducing cloud uniformity. At the same time, the pipes and nozzles are also prone to low-temperature icing and blockage under icing conditions, further hindering uniform diffusion and causing the cloud to deviate from the icing environment of the aero-engine icing test.

[0005] In such cases, it is generally necessary to redesign and adjust the spraying device to meet the requirements of different test points. This results in extremely poor versatility of the spraying device, requiring a significant amount of design analysis, installation, commissioning, and testing work, and increasing equipment costs. Summary of the Invention

[0006] This invention provides a cloud diffusion enhancement device and a high-altitude simulated icing test stand for aircraft engine icing tests, in order to solve the technical problem that when the flow rate of the existing test device increases, the cloud particles ejected from the nozzle are very easy to form bundles and are difficult to diffuse during the flow towards the engine, resulting in a significant reduction in cloud uniformity and the cloud deviating from the icing environment of aircraft engine icing tests.

[0007] The technical solution adopted in this invention is as follows:

[0008] A cloud diffusion enhancement device for aircraft engine icing tests includes: a spray device and several diffusion enhancement vortex generators; the spray device is installed in the air intake port of the high-altitude simulation chamber of a high-altitude simulated icing test stand, and includes several atomizing nozzles facing the inlet of the test engine inside the high-altitude simulation chamber; the spray device is used to atomize the supplied water under the action of the supplied compressed air to form cloud particles, which are then dispersed and sprayed outward by the several atomizing nozzles; the several diffusion enhancement vortex generators are installed one-to-one on the spray ends of the several atomizing nozzles, and each diffusion enhancement vortex generator is provided with several through-holes; the diffusion enhancement vortex generators are used to allow the high-speed main airflow entering from the air intake port of the high-altitude simulation chamber to pass through the several airflow through-holes and form a low-speed vortex zone on the back of the diffusion enhancement vortex generator, thereby driving the cloud particles sprayed by the corresponding atomizing nozzles to flow back with the vortex and diffuse outward to the edge of the diffusion enhancement vortex generator, so as to merge with the high-speed main airflow and spray it towards the test engine.

[0009] Furthermore, the spray device includes a spray bracket that serves as a mounting support, and multiple sets of atomizing tubes for atomizing the supplied water into cloud-like particles under the action of supplied compressed air and spraying them outward; the spray bracket is hollow and annular for installation in the air intake port of the high-altitude simulation chamber; multiple sets of atomizing tubes are sequentially spaced along the height direction on the spray bracket, and each set of atomizing tubes includes multiple atomizing nozzles sequentially spaced along its length direction, with the multiple atomizing nozzles on adjacent sets of atomizing tubes staggered one by one.

[0010] Furthermore, the distance between two adjacent atomizing tube groups is equal to the distance between two adjacent atomizing nozzles on the same atomizing tube group, and the distance is set as A. The outer diameter of the diffusion-enhancing vortex generator is set as B. Then: B = (0.4~0.6)A.

[0011] Furthermore, the diffusion-enhancing vortex generator includes a hollow disc-shaped vortex disk and a clamp for detachably fixing the vortex disk to the atomizing nozzle; the vortex disk is installed on the outer circle of the spray end of the atomizing nozzle through its central shaft hole, and is clamped and fixed to the spray end of the atomizing nozzle by the clamp; the vortex disk is also provided with a number of regularly arranged airflow penetration holes.

[0012] Furthermore, several airflow penetration holes are arranged in multiple concentric circles, and each concentric circle has multiple airflow penetration holes arranged sequentially and at intervals along the circumference; the distance between two adjacent concentric circles is 7-12 mm, the distance between two adjacent airflow penetration holes on the same concentric circle is 7-12 mm, and the multiple airflow penetration holes on two adjacent concentric circles are staggered one by one; each airflow penetration hole extends obliquely upward from the inlet side to the outlet side of the high-speed main airflow, so as to form an angle of 30° to 50° with the cloud and mist particle flow ejected by the atomizing nozzle, and the diameter of each airflow penetration hole is 2-5 mm.

[0013] Furthermore, the vortex disk is also provided with a ring of multiple de-icing air holes that run through it. The ring of multiple de-icing air holes is located in the innermost ring of the multiple concentric circles of airflow penetration holes and is located close to the outer wall of the atomizing nozzle. The de-icing air holes are used to guide air to blow towards the outer wall of the atomizing nozzle and the injection port to prevent icing.

[0014] Furthermore, the vortex disk includes a central mounting cylinder, a vortex plate fitted onto the outer circle of the mounting cylinder with its end face flush with one of the end faces of the mounting cylinder, and a reinforcing ring rib perpendicularly connected to the edge of the vortex plate and extending axially into an annular shape; the vortex disk is also split in half to form an upper vortex disk and a lower vortex disk, so that they are fitted onto the outer circle of the atomizing nozzle's spray end by the mating mounting cylinder; airflow penetration holes and de-icing blowing holes are respectively opened on the vortex plate.

[0015] Furthermore, each atomizing tube assembly includes a heat-insulating covering cylinder arranged transversely on opposite sides of the spray support, a water supply pipe and an air supply pipe arranged along the length of the heat-insulating covering cylinder, and heat-insulating material filled in the heat-insulating covering cylinder; multiple atomizing nozzles are arranged sequentially at intervals along the length of the heat-insulating covering cylinder, and the inner end of each atomizing nozzle located in the heat-insulating covering cylinder is connected to the water supply pipe and the air supply pipe, and the outer end of each atomizing nozzle extends out of the heat-insulating covering cylinder; at least one end of both the water supply pipe and the air supply pipe extends out of the spray support to introduce water and compressed air accordingly.

[0016] Furthermore, the spray support includes a hollow annular mounting ring and multiple sets of support cylinders corresponding to multiple sets of atomizing tubes; the mounting ring is used to fix in the air inlet of the high-altitude simulation chamber for installing the atomizing tubes and for allowing the airflow of the high-altitude simulation chamber to pass through; each set of support cylinders includes two support cylinders fixed on both sides of the mounting ring, the atomizing tubes are arranged laterally in the mounting ring and both ends extend into the two support cylinders on both sides for positioning and support, and at least one end of the water supply pipe and the air supply pipe extends outward after passing through the heat insulation covering cylinder and the support cylinder in sequence along the axial direction.

[0017] According to another aspect of the present invention, a high-altitude simulated icing test stand is also provided, comprising a high-altitude simulation chamber and a cloud diffusion enhancement device for aircraft engine icing test, as described above, disposed in the air intake port of the high-altitude simulation chamber.

[0018] The present invention has the following beneficial effects:

[0019] This invention's device is highly adaptable. When the diffusion-enhancing vortex generator is not installed on the atomizing nozzle, the device is suitable for windless or low-speed airflow conditions. When the diffusion-enhancing vortex generator is installed on the atomizing nozzle, the diffusion of the cloud particles ejected from the atomizing nozzle is enhanced through its function, thereby improving the uniformity of cloud particles at the engine inlet during aero-engine icing tests. This effectively solves the technical problem of poor cloud uniformity caused by the low inertia of cloud particles in high-speed airflow during aero-engine icing tests, thus adapting to various operating conditions with different flow rates. Furthermore, compared to traditional methods, which require extensive design analysis, installation, debugging, and testing work to conduct tests under different icing conditions, increasing design analysis work and equipment costs, this device, through the installation of the diffusion-enhancing vortex generator, adapts to different flow rates, thereby greatly reducing equipment costs and the amount of debugging work required.

[0020] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0021] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0022] Figure 1 This is a schematic diagram illustrating the principle of constructing an icing cloud environment for aircraft engines.

[0023] Figure 2 This is a schematic diagram of an existing spraying device;

[0024] Figure 3 This is a partial front view schematic diagram of the cloud diffusion enhancement device for aircraft engine icing test according to a preferred embodiment of the present invention;

[0025] Figure 4 yes Figure 3 Schematic diagram of the working principle of a diffusion-enhanced vortex generator;

[0026] Figure 5 yes Figure 4 Schematic diagram of the main structural dimensions of the diffusion-enhanced vortex generator;

[0027] Figure 6 yes Figure 5 A schematic diagram of the AA-direction cross-section structure;

[0028] Figure 7 yes Figure 3A schematic diagram of a half-structured diffusion-enhanced vortex generator.

[0029] Figure 8 yes Figure 3 Schematic diagram of the spatial structure of the central spray device;

[0030] Figure 9 yes Figure 8 A partial structural diagram of the spray device.

[0031] Legend:

[0032] 1. Spray bracket; 11. Mounting ring; 12. Support cylinder; 121. Support cylinder body; 122. Mounting flange; 123. Support end plate; 1230. Slot;

[0033] 2. Atomizing tube assembly; 21. Heat insulation covering cylinder; 2111. Upper airfoil plate; 2112. Lower airfoil plate; 212. Support plate; 22. Atomizing nozzle; 23. Water supply pipe; 24. Air supply pipe;

[0034] 3. Diffusion-enhanced vortex generator; 301. Airflow penetration hole; 302. De-icing air blowing hole; 31. Vortex disk; 311. Mounting cylinder; 312. Vortex plate; 313. Reinforcing ring rib; 314. Upper half of the vortex disk; 315. Lower half of the vortex disk; 32. Clamp;

[0035] 4. High-altitude simulation chamber; 5. Test engine. Detailed Implementation

[0036] The embodiments of the present invention will be 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. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0037] Those skilled in the art will understand that, unless specifically stated otherwise, the term "comprising" as used in this specification means the presence of the stated features, integers, steps, operations, components, and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, components, and / or combinations thereof. It should be understood that when we say a component is "connected" to another component, it can be directly connected to the other component or connected via an intermediate component. The term "and / or" as used herein includes all or any unit and all combinations of one or more associated listed items. The terms "first" and "second," etc., in this specification and claims are used to distinguish different objects, not to describe a particular order.

[0038] Reference Figure 3 and Figure 4 A preferred embodiment of the present invention provides a cloud diffusion enhancement device for aircraft engine icing tests, comprising: a spray device and a plurality of diffusion enhancement vortex generators 3. The spray device is installed in the air intake port of the high-altitude simulation chamber 4 of the high-altitude simulated icing test stand. The spray device includes a plurality of atomizing nozzles 22 facing the inlet of the test engine 5 inside the high-altitude simulation chamber 4. The spray device is used to atomize the supplied water under the action of the supplied compressed air to form cloud particles, which are then dispersed and sprayed outward by the plurality of atomizing nozzles 22. Several diffusion-enhancing vortex generators 3 are installed one-to-one on the injection ends of several atomizing nozzles 22. Each diffusion-enhancing vortex generator 3 is provided with several through-holes 301. The diffusion-enhancing vortex generator 3 is used to allow the high-speed main airflow entering from the air intake port of the high-altitude simulation cabin 4 to pass through several airflow through-holes 301 and form a low-speed vortex zone on the back of the diffusion-enhancing vortex generator 3. This, in turn, drives the cloud particles ejected by the corresponding atomizing nozzles 22 to flow back with the vortex and flow outward to the edge of the diffusion-enhancing vortex generator 3 to merge with the high-speed main airflow and then spray it toward the test engine 5.

[0039] In the cloud and fog diffusion enhancement device of the present invention, such as Figure 3 As shown, the spray bracket 1 is used to install and fix in the air inlet of the high-altitude simulation chamber 4 of the high-altitude simulated icing test stand. During operation, the water supplied from the outside is atomized into cloud particles by the compressed air supplied through the spray device and sprayed outward from several atomizing nozzles 22. At the same time, the high-speed main airflow also enters through the air inlet of the high-altitude simulation chamber 4. During the entry process, the airflow separates after passing through several airflow penetration holes 301 set on the diffusion enhancement vortex generator 3, and a low-speed vortex zone is formed on the back of the diffusion enhancement vortex generator 3 (such as...). Figure 4 As shown in the diagram, the airflow velocity in the vortex region is low. Some of the cloud particles ejected by the atomizing nozzle 22 first flow back with the vortex, and then flow outward to diffuse towards the outer edge of the diffusion enhancement vortex device 3. After diffusion, they merge with the high-speed main airflow to form an icing cloud environment, and are then sprayed at high speed towards the test engine 5 and sucked into the test engine 5, so that the test engine 5 is always in an icing environment (an ultracooled cloud particle environment), thereby testing the anti-icing capability of the aero-engine.

[0040] The device of this invention has strong applicability. When the diffusion-enhancing vortex generator 3 is not installed on the atomizing nozzle 22, the device is suitable for windless or low airflow speed conditions. When the diffusion-enhancing vortex generator 3 is installed on the atomizing nozzle 22, the diffusion of the cloud particles ejected from the atomizing nozzle 22 is enhanced through the action of the diffusion-enhancing vortex generator 3, thereby improving the uniformity of cloud particles at the engine inlet during aero-engine icing tests. This effectively solves the technical problem of poor cloud uniformity in aero-engine icing tests due to the small inertia of cloud particles in high-speed airflow. It is also adaptable to various operating conditions with different flow rates. At the same time, compared with the traditional solution, conducting tests under different icing conditions requires a lot of design analysis, installation, debugging, and testing work, increasing design analysis work and equipment costs. However, the device of this application, through the setting of the diffusion-enhancing vortex generator 3, enables the device to adapt to different flow rates, thereby greatly reducing equipment costs and a lot of debugging work.

[0041] Optionally, such as Figure 3 and Figure 8 As shown, the spray device includes a spray bracket 1 that serves as a support for installation, and multiple sets of atomizing tubes 2 for atomizing the supplied water into cloud particles under the action of supplied compressed air and spraying them outward. The spray bracket 1 is hollow and annular, designed for installation in the air inlet of the high-altitude simulation chamber 4. The spray bracket 1 is used to install the multiple sets of atomizing tubes 2 and also facilitates the passage of high-speed main airflow. The multiple sets of atomizing tubes 2 are sequentially spaced along the height direction on the spray bracket 1, and each set of atomizing tubes 2 includes multiple atomizing nozzles 22 sequentially spaced along its length direction. The multiple atomizing nozzles 22 on adjacent sets of atomizing tubes 2 are staggered to further enhance the diffusion of cloud particles and improve the uniformity of the cloud.

[0042] Preferably, such as Figure 3 As shown, the distance between two adjacent atomizing tube groups 2 is equal to the distance between two adjacent atomizing nozzles 22 on the same atomizing tube group 2, and both distances are set as A. The outer diameter of the diffusion enhancement vortex 3 is set as B. Then: B = (0.4~0.6)A. Within this range, the diffusion enhancement vortex 3 has the most significant effect on the diffusion of cloud and fog particles. Otherwise, if the value of B is too small (i.e., the gap between the diffusion enhancement vortex 3 is large), the particles will not have enough diffusion space and will be difficult to diffuse to the entire space. If the value of B is too large (i.e., the gap between the diffusion enhancement vortex 3 is small), it will increase the flow resistance in the high-altitude simulation cabin 4. In extreme cases, it will block the airflow channel. All of these will have an adverse effect on the diffusion of cloud and fog particles.

[0043] Optionally, such as Figure 5 and Figure 6As shown, the diffusion-enhancing vortex generator 3 includes a hollow, disc-shaped vortex disk 31 and a clamp 32 for detachably fixing the vortex disk 31 to the atomizing nozzle 22. The vortex disk 31 is mounted on the outer circumference of the spray end of the atomizing nozzle 22 through its central shaft hole, and is clamped and fixed to the spray end of the atomizing nozzle 22 by the clamp 32. The vortex disk 31 is also provided with a number of regularly arranged airflow penetration holes 301.

[0044] In this optional solution, such as Figure 5 and Figure 6 As shown, several airflow penetration holes 301 are arranged in multiple concentric circles, and each concentric circle has multiple airflow penetration holes 301 arranged at intervals along the circumference. The distance between two adjacent concentric circles is 7-12 mm, and the distance between two adjacent airflow penetration holes 301 on the same concentric circle is 7-12 mm. The multiple airflow penetration holes 301 on two adjacent concentric circles are staggered. This structural dimension setting can ensure that the entire vortex disk 31 area is covered by the outwardly ejected airflow, preventing local dead zones without airflow from affecting particle diffusion and particle retention and icing. In actual design, the optimal distance between two adjacent concentric circles is 10 mm, and the optimal distance between two adjacent airflow penetration holes 301 on the same concentric circle is also 10 mm. Each airflow penetration hole 301 extends obliquely upward from the inlet side to the outlet side of the high-speed main airflow, forming an angle of 30° to 50° with the cloud particle stream ejected by the atomizing nozzle 22. The diameter of each airflow penetration hole 301 is 2 to 5 mm. If the angle is too small, the axial velocity of the airflow will be insufficient to propel the cloud particles forward, causing them to collide with the vortex generator and adhere to it, forming ice. If the angle is too large, the outward velocity of the airflow will be insufficient, weakening the particle diffusion effect. When the angle is exactly 90°, there is no diffusion effect at all. If the diameter is too small, the airflow will be excessively decelerated, resulting in insufficient airflow propulsion and affecting the cloud particle diffusion effect. If the diameter is too large, it is impossible to arrange a sufficiently high density of holes, thus affecting the uniformity and consistency of the outward diffusion airflow, leading to uneven circumferential diffusion of particles. In actual design, the optimal angle between the airflow penetration hole 301 and the cloud particle stream ejected by the atomizing nozzle 22 is 45°, and the optimal diameter of each airflow penetration hole 301 is 4 mm.

[0045] During operation, these settings utilize high-speed main airflow to flow pressure, guiding the airflow to the outside of the diffusion-enhancing vortex 3 through the airflow penetration hole 301 inside the diffusion-enhancing vortex 3, forming an outwardly diffused radial airflow, which in turn pushes the cloud particles ejected from the atomizing nozzle 22 outward to further enhance the outward diffusion effect of the cloud particles; on the other hand, since the temperature around the diffusion-enhancing vortex 3 is low, cloud particles near the diffusion-enhancing vortex 3 may collide with the diffusion-enhancing vortex 3 and freeze on the diffusion-enhancing vortex 3, causing it to fail and block the atomizing nozzle 22. Through the setting of the airflow penetration hole 301, an isolation air film can be formed on the surface of the diffusion-enhancing vortex 3 to prevent cloud particles from adhering to the diffusion-enhancing vortex 3 (hereinafter referred to as "vortex") and the atomizing nozzle 22 and freezing.

[0046] Preferably, such as Figure 6 As shown, the vortex disk 31 also has a plurality of de-icing air holes 302 arranged in a ring. The plurality of de-icing air holes 302 are located in the innermost ring of the multiple concentric circles of airflow penetration holes 301 and are located close to the outer wall of the atomizing nozzle 22. The de-icing air holes 302 are used to guide air to blow towards the outer wall of the atomizing nozzle 22 and the injection port to prevent icing. At the same time, by setting the de-icing air holes 302 on the vortex, cloud particles near the atomizing nozzle 22 are blown out, further preventing cloud particles from icing on the atomizing nozzle 22.

[0047] In this optional solution, such as Figure 6 and Figure 7 As shown, the vortex disk 31 includes a centrally located mounting cylinder 311, a vortex plate 312 fitted onto the outer circumference of the mounting cylinder 311 with its end face flush with one of the end faces of the mounting cylinder 311, and a reinforcing ring rib 313 vertically connected to the edge of the vortex plate 312 and extending axially into an annular shape. The vortex disk 31 is also split in half to form an upper vortex disk 314 and a lower vortex disk 315, so that they can be fitted onto the outer circumference of the spray end of the atomizing nozzle 22 by the mating mounting cylinder 311. This structure facilitates the installation of the vortex generator on the atomizing nozzle 22 and allows for experimental installation and modification without changing the existing structure of the atomizing nozzle 22, avoiding the need to redesign and manufacture the spray system. An airflow penetration hole 301 and a de-icing blowing hole 302 are respectively formed on the vortex plate 312.

[0048] Optionally, such as Figure 8As shown, each atomizing tube group 2 includes a heat-insulating covering cylinder 21 transversely passing through the spray support 1 on opposite sides, a water supply pipe 23 and an air supply pipe 24 arranged along the length of the heat-insulating covering cylinder 21, and heat-insulating material filled inside the heat-insulating covering cylinder 21. Multiple atomizing nozzles 22 are arranged sequentially at intervals along the length of the heat-insulating covering cylinder 21, with the inner end of each atomizing nozzle 22 connected to the water supply pipe 23 and the air supply pipe 24, and the outer ends of each atomizing nozzle 22 extending out of the heat-insulating covering cylinder 21. At least one end of both the water supply pipe 23 and the air supply pipe 24 extends out of the spray support 1 to correspondingly introduce water and compressed air. In the spray device of the present invention, each atomizing tube group 2 includes a heat-insulating covering cylinder 21 and heat-insulating material filled in the heat-insulating covering cylinder 21. The water supply pipe 23 and the air supply pipe 24 are covered between the heat-insulating covering cylinder 21 and the heat-insulating material (polyurethane foam, heat insulation cotton or heat tracing cable, etc.), thereby greatly reducing the thermal conductivity between the main airflow cold air entering from the air inlet of the high-altitude simulation chamber 4 and the water supply pipe 23 and the air supply pipe 24, thereby improving the anti-freezing and anti-blocking ability of the water supply pipe 23 and the air supply pipe 24 during the test to prevent icing, so as to form cloud mist particles in the atomizing nozzle 22 and smoothly spray out and diffuse from the atomizing nozzle 22.

[0049] Optionally, such as Figure 8 As shown, the spray bracket 1 includes a hollow annular mounting ring 11 and multiple sets of support cylinders corresponding to multiple sets of atomizing tube assemblies 2. The mounting ring 11 is used to fix in the air inlet of the high-altitude simulation chamber 4 for mounting the atomizing tube assemblies 2 and for allowing the airflow of the high-altitude simulation chamber 4 to pass through. Each set of support cylinders includes two support cylinders 12 fixed on both sides of the mounting ring 11. The atomizing tube assembly 2 is arranged laterally inside the mounting ring 11 and its two ends extend into the two support cylinders 12 on both sides for positioning and support. At least one end of the water supply pipe 23 and the air supply pipe 24 passes through the heat insulation covering cylinder 21 and the support cylinder 12 in sequence along the axial direction and then extends outward.

[0050] In this optional solution, such as Figure 8 and Figure 9As shown, the heat-insulating covering cylinder 21 includes a hollow covering cylinder body and two support plates 212 detachably connected to both ends of the covering cylinder body to close the covering cylinder body. The support cylinder 12 includes a support cylinder body 121 with one end fixed to the outer wall of the mounting ring 11 and the other end cantilevered, a mounting flange 122 fixed to the cantilevered end of the support cylinder body 121, and a support end plate 123 fixed in cooperation with the mounting flange 122. The support end plate 123 is recessed into the inner side wall of the mounting flange 122 to form a groove 1230. The atomizing tube assembly 2 is supported and positioned in the two support cylinders 12 by the cooperation of the support plates 212 at both ends with the corresponding grooves 1230. When maintenance is required on the atomizing nozzle 22, air supply pipe 24, and water supply pipe 23, the support end plates 123 at both ends can be removed first, the atomizing tube assembly 2 can be taken out, and then the atomizing tube assembly 2 can be disassembled to perform internal maintenance on the atomizing nozzle 22. Parts can be repaired or replaced as needed, and the cost of use can be reduced by modifying and maintaining the equipment.

[0051] Preferably, such as Figure 8 and Figure 9 As shown, the heat-insulating covering cylinder 21 is an airfoil-shaped cylinder with an airfoil-shaped cross-section. When the atomizing tube assembly 2 is located in the air intake path of the high-speed cold airflow at the air intake port of the high-altitude simulation cabin 4, the airfoil-shaped setting of the heat-insulating covering cylinder 21 can effectively reduce the disturbance of the high-speed airflow by the atomizing tube assembly 2. The airfoil cylinder includes an upper airfoil plate 2111 and a lower airfoil plate 2112 arranged opposite to each other, and multiple sets of fasteners for detachably fixing the upper airfoil plate 2111 and the lower airfoil plate 2112. In this preferred embodiment, the detachable setting of the airfoil cylinder facilitates in-depth maintenance of the atomizing nozzle 22 and the pipeline.

[0052] Reference Figure 1 A preferred embodiment of the present invention also provides a high-altitude simulated icing test stand, including a high-altitude simulation chamber 4 and a cloud diffusion enhancement device for aero-engine icing tests, as described above, disposed in the air inlet port of the high-altitude simulation chamber 4. Therefore, the device of the present invention has strong applicability. When the diffusion enhancement vortex 3 is not installed on the atomizing nozzle 22, it can be used in windless or low airflow speed conditions. When the diffusion enhancement vortex 3 is installed on the atomizing nozzle 22, the diffusion of cloud particles ejected from the atomizing nozzle 22 is enhanced through the action of the diffusion enhancement vortex 3, thereby improving the uniformity of cloud particles at the engine inlet during aero-engine icing tests. This effectively solves the technical problem of poor cloud uniformity in aero-engine icing tests due to the low inertia of cloud particles in high-speed airflow. Furthermore, the installation of the diffusion enhancement vortex 3 allows the device to adapt to different flow rates, thereby greatly reducing equipment costs and a large amount of debugging work.

[0053] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A cloud diffusion enhancement device for aircraft engine icing tests, characterized in that, include: Spraying device and several diffusion-enhancing vortex generators (3); The spray device is installed in the air inlet of the high-altitude simulation chamber (4) of the high-altitude simulation icing test stand. The spray device includes several atomizing nozzles (22) facing the inlet of the test engine (5) inside the high-altitude simulation chamber (4). The spray device is used to atomize the supplied water under the action of the supplied compressed air to form cloud particles and disperse them outward by several atomizing nozzles (22). Several diffusion-enhancing vortex generators (3) are installed one-to-one on the injection ends of several atomizing nozzles (22). Each diffusion-enhancing vortex generator (3) is provided with several through-holes (301). The diffusion-enhancing vortex generator (3) is used to allow the high-speed main airflow entering from the air intake port of the high-altitude simulation cabin (4) to pass through several airflow through-holes (301) and form a low-speed vortex zone on the back of the diffusion-enhancing vortex generator (3). This, in turn, drives the cloud particles ejected by the corresponding atomizing nozzles (22) to flow back with the vortex and flow outward to the edge of the diffusion-enhancing vortex generator (3) to merge with the high-speed main airflow and then spray it toward the test engine (5). The diffusion-enhancing vortex generator (3) includes a hollow disc-shaped vortex disk (31) and a clamp (32) for detachably fixing the vortex disk (31) to the atomizing nozzle (22); the vortex disk (31) is installed on the outer circle of the spray end of the atomizing nozzle (22) through the shaft hole in its center, and is clamped and fixed to the spray end of the atomizing nozzle (22) by the clamp (32); the vortex disk (31) is also provided with a number of regularly arranged airflow penetration holes (301). A number of airflow penetration holes (301) are arranged in multiple concentric circles, and each concentric circle has multiple airflow penetration holes (301) arranged sequentially along the circumference; the distance between two adjacent concentric circles is 7 to 12 mm, the distance between two adjacent airflow penetration holes (301) on the same concentric circle is 7 to 12 mm, and multiple airflow penetration holes (301) on two adjacent concentric circles are staggered; each airflow penetration hole (301) extends obliquely upward from the inlet side to the outlet side of the high-speed main airflow, so as to form an angle of 30° to 50° with the cloud and mist particle flow sprayed by the atomizing nozzle (22), and the diameter of each airflow penetration hole (301) is 2 to 5 mm.

2. The cloud diffusion enhancement device for aero-engine icing testing according to claim 1, characterized in that, The spraying device includes a spray support bracket (1) for mounting and supporting, and multiple sets of atomizing tubes (2) for atomizing the supplied water into cloud particles under the action of the supplied compressed air and spraying them outward. The spray bracket (1) is hollow and ring-shaped for installation in the air intake port of the high-altitude simulation chamber (4); Multiple atomizing tube groups (2) are sequentially and spaced apart on the spray bracket (1) along the height direction, and each atomizing tube group (2) includes multiple atomizing nozzles (22) sequentially and spaced apart along its length direction, and the multiple atomizing nozzles on two adjacent atomizing tube groups (2) are staggered one by one.

3. The cloud diffusion enhancement device for aero-engine icing testing according to claim 2, characterized in that, The distance between two adjacent atomizing tube groups (2) is equal to the distance between two adjacent atomizing nozzles (22) on the same atomizing tube group (2), and both distances are set as A. The outer diameter of the diffusion-enhancing vortex generator (3) is set as B. Then: B = (0.4 ~ 0.6)A.

4. The cloud and fog diffusion enhancement device for aircraft engine icing tests according to claim 1, characterized in that, The vortex disk (31) is also provided with a ring of multiple de-icing air holes (302) that run through it. The ring of multiple de-icing air holes (302) is located in the innermost ring of the multiple concentric airflow penetration holes (301) and is located close to the outer wall of the atomizing nozzle (22). The de-icing air hole (302) is used to direct air towards the outer wall of the atomizing nozzle (22) and the spray port to prevent icing.

5. The cloud diffusion enhancement device for aero-engine icing testing according to claim 4, characterized in that, The vortex plate (31) includes a central mounting cylinder (311), a vortex plate (312) fitted on the outer circle of the mounting cylinder (311) and having its end face flush with one of the end faces of the mounting cylinder (311), and a reinforcing ring rib (313) that is vertically connected to the edge of the vortex plate (312) and extends axially into an annular shape. The vortex disk (31) is further split in half to form an upper vortex disk (314) and a lower vortex disk (315), which are fitted onto the outer circle of the spray end of the atomizing nozzle (22) by a mating mounting cylinder (311). The airflow penetration hole (301) and the de-icing blowing hole (302) are respectively opened on the vortex plate (312).

6. The cloud diffusion enhancement device for aero-engine icing testing according to claim 2, characterized in that, Each atomizing tube group (2) includes a heat insulation covering cylinder (21) arranged on opposite sides of the spray bracket (1) in the transverse direction, a water supply pipe (23) and an air supply pipe (24) arranged in the heat insulation covering cylinder (21) along the length direction of the heat insulation covering cylinder (21), and heat insulation material filled in the heat insulation covering cylinder (21); Multiple atomizing nozzles (22) are arranged sequentially at intervals along the length of the heat insulation covering cylinder (21), and the inner end of each atomizing nozzle (22) located in the heat insulation covering cylinder (21) is connected to the water supply pipe (23) and the air supply pipe (24), and the outer end of each atomizing nozzle (22) extends out of the heat insulation covering cylinder (21). At least one end of both the water supply pipe (23) and the air supply pipe (24) extends out of the spray bracket (1) to introduce water and compressed air respectively.

7. The cloud diffusion enhancement device for aircraft engine icing test according to claim 6, characterized in that, The spray bracket (1) includes a hollow annular mounting ring (11) and multiple sets of support cylinders corresponding to multiple sets of atomizing tubes (2); The mounting ring (11) is used to fix it in the air inlet of the high-altitude simulation chamber (4) for installing the atomizing tube assembly (2) and for the air intake airflow of the high-altitude simulation chamber (4) to pass through; Each set of support cylinders includes two support cylinders (12) fixed on both sides of the mounting ring (11). The atomizing tube group (2) is arranged in the mounting ring (11) and its two ends extend into the two support cylinders (12) on both sides for positioning and support. At least one end of the water supply pipe (23) and the air supply pipe (24) are sequentially inserted through the heat insulation covering cylinder (21) and the support cylinder (12) along the axial direction and then extend outward.

8. A high-altitude simulated icing test stand, characterized in that, It includes a high-altitude simulation chamber (4) and a cloud diffusion enhancement device for aircraft engine icing test as described in any one of claims 1-7, which is installed in the air intake port of the high-altitude simulation chamber (4).

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