Flow channel simulation part, anti-icing test device and anti-icing test method

Abstract

The present invention provides a flow path simulation component, an anti-icing test device and an anti-icing test method. The flow path simulation component includes an outer wall, an inner wall, a channel and a plurality of support members. The outer wall is a rotating body, and the upstream end of the outer wall is used to connect to a splitter ring test piece; the inner wall is a rotating body and is located radially inside the outer wall; the channel is formed between the outer wall and the inner wall and is used to connect to a suction device to simulate the core duct airflow of a compressor of a turbofan engine; the plurality of support members are evenly distributed in the circumferential direction of the outer wall and the inner wall, and the two ends are respectively connected to the outer wall and the inner wall. The anti-icing test device includes a first fan, a second fan and the flow path simulation component. The first fan is used to simulate the bypass duct airflow of a compressor of a turbofan engine, and the second fan is connected to the downstream side of the channel and is used to provide the suction device. The anti-icing test method uses the anti-icing test device, and designs the upstream side area and the downstream side area of the channel according to the maximum suction volume of the second fan and the maximum speed of the core duct airflow required for the test.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengine test, and particularly relates to a flow path simulation component, an anti-icing test device and an anti-icing test method. Background Art

[0002] Since clouds may contain metastable supercooled liquid water with a temperature lower than the freezing point, when an aircraft passes through these clouds, icing is likely to occur on the surfaces of the windward components of the aircraft. For the aeroengine intake components, such as intake fairings, fan blades, intake struts and engine splitter rings, etc., since the air flow will accelerate and cool down when being sucked by the engine, the probability of icing is even greater. Icing will deteriorate the starting performance of components, and at the same time cause the center of gravity of the rotating components to shift and intensify vibration, and these phenomena are very unfavorable for flight safety. Therefore, anti-icing systems are generally configured on the currently in-service aircraft and their engines.

[0003] The hot air anti-icing system is currently the most mature and widely used anti-icing system. It mainly extracts hot air from the engine air system, and transports the hot air to the inner cavity of the anti-icing component through specific pipelines and valves, so as to achieve the purpose of raising the surface temperature of the anti-icing component and preventing the surface of the anti-icing component from icing. The anti-icing bleed air usually merges into other air system flow paths after flowing out of the anti-icing cavity, or is directly discharged to the external atmosphere and the engine main flow path.

[0004] The splitter ring of a turbofan engine is a typical anti-icing component, and its anti-icing form is usually hot air anti-icing. In order to verify the hot air anti-icing effect of the splitter ring, it is necessary to carry out the hot air anti-icing test of the splitter ring in an icing wind tunnel. Parameters such as the water droplet diameter, liquid water content, velocity, ambient temperature and pressure in the atmosphere can be simulated in the icing wind tunnel. By placing the test piece in the icing wind tunnel, simulating the atmospheric icing environment outside the test piece, and taking heating measures (hot air or electric current) inside the test piece, etc., the tests of wall temperature, cavity temperature, cavity pressure, etc. can be carried out to complete the anti-icing test. The test parameters obtained from the test can be used to guide the design of the aeroengine anti-icing system.

[0005] Since the splitter ring is a component that separates the core duct and the bypass duct of the engine, in the actual engine structure, the high-speed rotation of the engine causes the air flow to flow through the upper and lower surfaces of the splitter ring at a high speed. At the same time, due to the different gas flow rates in the core duct and the bypass duct, the flow velocities on the upper and lower surfaces of the splitter ring are inconsistent, and it is difficult to simultaneously simulate the flow velocities on the upper and lower surfaces of the splitter ring by the existing fans in the wind tunnel. Summary of the Invention

[0006] An object of the present invention is to provide a flow path simulation component, which can simulate the core duct air flow of the compressor of a turbofan engine.

[0007] The flow channel simulation part for achieving the above object is used for the anti-icing test of the splitter ring of a turbofan engine, and includes an outer wall, an inner wall, a channel and a plurality of support members. The outer wall is a rotating body, and the upstream end of the outer wall is used to connect the splitter ring test part; the inner wall, which is a rotating body, is located radially inside the outer wall; the channel is formed between the outer wall and the inner wall and is used to connect a suction device to simulate the core flow of the compressor of the turbofan engine; the plurality of support members are evenly distributed in the circumferential direction of the outer wall and the inner wall, and both ends of the support member are respectively connected to the outer wall and the inner wall.

[0008] In one or more embodiments of the flow channel simulation part, the flow channel simulation part further includes a plurality of through holes, the plurality of through holes are evenly distributed in the circumferential direction of the flow channel simulation part and penetrate through the inner wall, the outer wall and the support member, wherein each support member corresponds to at least one through hole.

[0009] In one or more embodiments of the flow channel simulation part, the upstream side area of the channel is larger than the downstream side area.

[0010] In one or more embodiments of the flow channel simulation part, the support member is an airfoil structure.

[0011] In one or more embodiments of the flow channel simulation part, the direction from the leading edge to the trailing edge of the airfoil structure is parallel to the direction from the upstream side to the downstream side of the channel.

[0012] In one or more embodiments of the flow channel simulation part, the number of the support members is not less than 6 and not more than 10.

[0013] In one or more embodiments of the flow channel simulation part, the outer wall and the inner wall are respectively provided with an outer mounting hole and an inner mounting hole, the outer mounting hole and the inner mounting hole correspond to the cross-sectional shape of the plurality of support members, and both ends of the support member are respectively inserted into the outer mounting hole and the inner mounting hole and are respectively welded to the outer wall and the inner wall.

[0014] In one or more embodiments of the flow channel simulation part, the support member is perpendicular to the outer wall or / and the inner wall.

[0015] The flow channel simulation component can simulate the flow channel of the booster stage of the compressor of a corresponding model of turbofan engine, and then effectively simulate the core flow of the corresponding compressor by connecting to the second fan. Under static conditions, the flow field effect of the high-speed rotation of the multi-stage rotor blades of an actual engine can be achieved, so that the gas flow velocity on the lower surface of the splitter ring test component is consistent with the actual flow velocity under the established working conditions corresponding to the anti-icing test, and it can also support the splitter ring test component. The structure of the flow channel simulation component is simple, easy to machine, manufacture and assemble, and can effectively reduce the design, machining and test costs.

[0016] Another object of the present invention is to provide an anti-icing test device that can simultaneously simulate the core flow and the bypass flow of the compressor of a turbofan engine.

[0017] The anti-icing test device for achieving the above object includes a first fan, a second fan and the aforementioned flow channel simulation component. The first fan is used to simulate the bypass flow of the compressor of the turbofan engine, and the second fan is used to provide the suction device. The second fan is connected to the downstream side of the channel.

[0018] In one or more embodiments of the anti-icing test device, the flow channel simulation component further includes a plurality of through holes, which are evenly distributed in the circumferential direction of the flow channel simulation component and penetrate the inner wall, the outer wall and the support member. Wherein, each support member corresponds to at least one through hole. The anti-icing test device further includes a detection element, a test lead and a test bench. The detection element is arranged on the splitter ring test component, and the test lead is communicatively connected to the detection element and the test bench. The test lead passes through one or more of the through holes.

[0019] The anti-icing test device can make the gas flow velocities on the upper surface and the lower surface of the splitter ring test component consistent with the actual flow velocities under the established working conditions by using the first fan to simulate the bypass flow of the compressor of a corresponding model of turbofan engine and connecting the second fan to the flow channel simulation component alone to simulate the core flow of the corresponding compressor. Thus, the anti-icing test of the splitter ring can be effectively carried out, the accuracy of the test results can be ensured, the test efficiency can be improved, and then the design of the anti-icing system can be effectively guided, the design cycle of the aeroengine can be shortened, and the safety and reliability of the aeroengine can be improved. The structure of the anti-icing test device is simple, easy to machine, manufacture and assemble, and can reduce the costs of design, machining and testing.

[0020] Yet another object of the present invention is to provide an anti-icing test method that can simultaneously simulate the core flow and the bypass flow of the compressor of a turbofan engine.

[0021] The anti-icing test method for achieving the above object uses the aforementioned anti-icing test device, and designs the upstream side area and the downstream side area of the channel according to the maximum suction volume of the second fan and the maximum velocity of the airflow in the core duct required for the test.

[0022] In one or more embodiments of the anti-icing test method, the profiles of the outer wall and the inner wall respectively simulate the profiles of the stator casing of the booster stage and the inner ring of the booster stage of the turbofan engine.

[0023] This anti-icing test method can simultaneously simulate the airflow in the bypass duct and the core duct of the turbofan engine, making the gas flow velocities on the upper and lower surfaces of the splitter ring test piece consistent with the actual flow velocities under the established working conditions. Thus, the anti-icing test of the splitter ring can be effectively carried out, ensuring the accuracy of the test results, improving the test efficiency, and further effectively guiding the design of the anti-icing system, shortening the design cycle of the aeroengine, and improving the safety and reliability of the aeroengine. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The above and other features, properties, and advantages of the present invention will become more apparent from the following description with reference to the drawings and embodiments, wherein:

[0025] Figure 1 is a partial schematic view of the compressor of a certain type of turbofan engine.

[0026] Figure 2 is a schematic view of the anti-icing test device.

[0027] Figure 3 and Figure 4 are three-dimensional schematic views of the flow path simulation part from different perspectives.

[0028] Figure 5 is a front view of the flow path simulation part.

[0029] Figure 6 is a side view of the flow path simulation part.

[0030] Figure 7 is a sectional view of the flow path simulation part.

[0031] Figure 8 is a three-dimensional schematic view of the outer wall of the flow path simulation part.

[0032] Figure 9 is a three-dimensional schematic view of the inner wall of the flow path simulation part.

[0033] Figure 10 is a three-dimensional schematic view of the support part of the flow path simulation part.

[0034] Figure 11 is a cross-sectional view of the support part of the flow path simulation part.

[0035] Figure 12 It is a schematic diagram of the connection relationship between the runner simulation part and some adjacent components. Specific embodiments

[0036] The following discloses various embodiments or examples for implementing the described subject technical solutions. To simplify the disclosure, specific examples of various elements and arrangements are described below. Of course, these are only examples and do not limit the protection scope of the present invention. It should be noted that the drawings are only examples and are not drawn under conditions of equal scale, and should not limit the actual claimed protection scope of the present invention. In addition, certain features, structures, or characteristics in one or more embodiments of the present application can be appropriately combined.

[0037] Figure 1 It shows a partial schematic diagram of a compressor 100 of a certain type of turbofan engine. The splitter ring 101 is located downstream of the inlet fan blade 102 of the compressor 100, and can separate the inlet air flow into two paths: the bypass air flow 103 and the core air flow 104. The core air flow 104 then enters the booster stage 105 located downstream of the splitter ring 101 and continues to flow downstream of the compressor 100 of the turbofan engine.

[0038] The booster stage 105 includes multiple stages of rotor blades 106 and multiple stages of stator blades 107. The rotor blades 106 are installed on the rotor disk hub 108. The two radial sides of the stator blades 107 are respectively connected to the booster stage stator casing 109 and the stator inner ring 110. The rotor disk hub 108 and the stator inner ring 110 together form the booster stage inner ring 111. The core air flow 104 flows in the flow path formed between the booster stage inner ring 111 and the booster stage stator casing 109.

[0039] In the description of the present invention, the terms "upstream" and "downstream" refer to the relative flow directions with respect to the fluid flow in the fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction to which the fluid flows.

[0040] The anti-icing test device 200 according to one or more embodiments of the present invention is as Figure 2As shown, it includes a wind tunnel 210 and a test bench 220. The wind tunnel 210 includes a first fan 201, a ventilation tower 202, a cooler 203, a water spraying device 204, a test section 205, etc. Inside the test section 205, there are provided a second fan (not shown), a splitter ring test piece (not shown), a flow path simulation piece 400 described later, a support device (not shown), a detection element (not shown), test leads 206, etc. The flow path simulation piece 400 is fixed inside the test section 205 through the support device. The first fan 201 is used to simulate the external duct air flow of the compressor of the turbofan engine corresponding to the splitter ring test piece. The second fan is connected to the downstream of the flow path simulation piece 400 and is used to simulate the internal duct air flow of the corresponding compressor, as described in detail later. The detection element is arranged on the splitter ring test piece and is communicably connected to the test bench 220 outside the wind tunnel 210 through the test leads 206.

[0041] The flow path simulation piece 400 is as Figures 3 to 7 shown and includes an outer wall 1, an inner wall 2, a channel 4, and a plurality of support members 3. Both the outer wall 1 and the inner wall 2 are of rotational symmetry, and the inner wall 2 is located radially inside the outer wall 1. The support members 3 are evenly distributed in the circumferential direction of the outer wall 1 and the inner wall 2, and both ends 31 of each support member 3 are respectively connected to the outer wall 1 and the inner wall 2. A channel 4 is formed between the outer wall 1 and the inner wall 2, and the downstream side 42 of the channel 4 is connected to the second fan to suck the gas in the channel 4 through the second fan, simulating the internal duct air flow of the compressor of the corresponding type of turbofan engine.

[0042] Both the upstream end 11 and the downstream end 12 of the outer wall 1 are provided with an outer wall mounting edge 13 and a plurality of outer wall bolt holes 14, where the upstream end 11 is used to connect to the splitter ring test piece, and the downstream end 12 is used to connect to other components inside the test section 205. Both axial ends of the inner wall 2 are provided with an inner wall mounting edge 21 and a plurality of inner wall bolt holes 22 for connecting to other components inside the test section 205.

[0043] Referring to Figure 12 , in one embodiment, the downstream end 12 of the outer wall 1 is connected to one end of a suction pipe 207 through the outer wall mounting edge 13, the other end of the suction pipe 207 is connected to the second fan through a bellows (not shown), and the mounting edge 21 of the inner wall 2 on the downstream side is connected to a plugging member 208. The plugging member 208 is used to plug the inner wall 2 so that the second fan only sucks the gas in the channel 4, thereby improving the suction efficiency and saving the power of the second fan. Optionally, the plugging member 208 is set in the shape of a rotational symmetry with a gradually decreasing diameter from upstream to downstream, so as to play a guiding role for the gas in the channel 4. In another embodiment, the plugging member 208 can also be integrally structured with the inner wall 2.

[0044] Referring to Figures 3 to 7, Optionally, the flow path simulation member 400 further includes a plurality of through holes 5. The plurality of through holes 5 are evenly distributed in the circumferential direction of the flow path simulation member 400 and penetrate through the outer wall 1, the inner wall 2 and the support member 3. Among them, each support member 3 corresponds to at least one through hole 5. Since a large number of detection elements need to be arranged in the splitter ring test piece during the anti-icing test, and the detection elements are communicably connected to the test bench 220 outside the wind tunnel 210 through the test leads 206. The test leads 206 directly exposed in the channel 4 are easily damaged by the high-speed air flow during the test, affecting the stability and accuracy of data transmission, and even causing the test to be suspended. By providing a plurality of through holes 5, the test leads 206 can pass through some or all of the through holes 5 as needed, thereby protecting the test leads 206, ensuring the test accuracy and test effect, reducing the weight of the flow path simulation member 400, and having a simple structure and being easy to process and manufacture.

[0045] The shape of the through hole 5 can be circular, or elliptical, or racetrack-shaped, or other shapes. By reasonably designing the number and size of the through holes 5, the requirements for protecting the test leads 206 and the strength requirements of the support member 3 can be satisfied simultaneously.

[0046] Optionally, the outer wall 1, the inner wall 2 and the plurality of support members 3 are made of stainless steel material, so that the flow path simulation member 400 has a high stiffness and can withstand the test conditions of low temperature and humidity, and is not prone to failure.

[0047] The flow path simulation member 400 can simulate the flow path of the booster stage of the compressor of the corresponding model of turbofan engine. Then, by connecting the second fan, the internal duct air flow of the corresponding compressor can be effectively simulated, and the flow field effect of the high-speed rotation of the multi-stage rotor blades of the actual engine can be achieved under static conditions, so that the gas flow velocity on the lower surface of the splitter ring test piece is consistent with the actual flow velocity under the established working conditions corresponding to the anti-icing test, and the splitter ring test piece can be supported. The structure of the flow path simulation member 400 is simple, easy to process, manufacture and assemble, and can effectively reduce the design, processing and test costs.

[0048] The flow path simulation member 400 is provided with a plurality of support members 3 between the outer wall 1 and the inner wall 2 to play a supporting role. Compared with the structure of the booster stage in the actual engine that uses multiple stator blades for support, the structure is simple, easy to process and manufacture, and the cost is low. Optionally, the support member 3 is perpendicular to or nearly perpendicular to the outer wall 1 or / and the inner wall 2 to improve the support strength. The number of the support members 3 can be designed to be 6 to 10, so as to minimize the influence on the flow area of the channel 4 while meeting the support strength requirements.

[0049] Refer to Figures 3 to 9, optionally, the outer wall 1 and the inner wall 2 are respectively provided with an outer mounting hole 15 and an inner mounting hole 23. The outer mounting hole 15 and the inner mounting hole 23 correspond to the cross-sectional shape of the support member 3. The two ends 31 of the support member 3 are respectively inserted into the outer mounting hole 15 and the inner mounting hole 23 and are respectively welded to the outer wall 1 and the inner wall 2, so as to further simplify the structure of the flow path simulation member 400 and facilitate processing and manufacturing. To facilitate the connection between the outer wall 1 and the inner wall 2, the two ends 31 of the support member 3 can slightly protrude from the radially outer side of the outer wall 1 and the radially inner side of the inner wall 2.

[0050] Referring to Figures 3 to 7 , Figure 10 , Figure 11 , optionally, the support member 3 is of an airfoil structure to reduce the air flow resistance in the channel 4. Compared with the blades with complex curved surface shapes of an actual engine, the structure is simple and easy to process and manufacture. Further, the direction from the leading edge 32 to the trailing edge 33 of the airfoil structure can be set to be substantially parallel to the direction from the upstream side 41 to the downstream side 42 of the channel 4, that is, substantially parallel to the air flow direction in the channel 4, so as to minimize the air flow resistance in the channel 4 to the greatest extent.

[0051] The anti-icing test device 200 simulates the external duct air flow of the compressor of a corresponding model turbofan engine by using the first fan 201, and connects the flow path simulation member 400 by separately arranging a second fan to simulate the internal duct air flow of the corresponding compressor, so that the gas flow velocities on the upper surface and the lower surface of the splitter ring test piece are consistent with the actual flow velocities under the established working conditions. Thus, the anti-icing test of the splitter ring can be effectively carried out, the accuracy of the test results can be ensured, the test efficiency can be improved, and further, the design of the anti-icing system can be effectively guided, the design cycle of the aeroengine can be shortened, and the safety and reliability of the aeroengine can be improved. The structure of the anti-icing test device 200 is simple, easy to process, manufacture and assemble, and can reduce the costs of design, processing and testing.

[0052] The anti-icing test method according to one or more embodiments of the present invention uses the aforementioned anti-icing test device 200. According to the maximum suction volume of the second fan and the maximum velocity of the internal duct air flow required for the test, the areas of the upstream side 41 and the downstream side 42 of the channel 4 are designed so that the air flow velocity in the channel 4 is consistent with the established working conditions, and the accuracy of the test results is improved.

[0053] Optionally, the area of the upstream side 41 of the channel 4 is larger than the area of the downstream side 42 to simulate the tapered flow path of the booster stage of a corresponding model turbofan engine, thereby further improving the accuracy of the test results.

[0054] The surfaces of the outer wall 1 and the inner wall 2 are smooth, and the profile is determined according to aerodynamic analysis to ensure the minimum pressure loss caused by the channel 4. Optionally, the profile of the outer wall 1 simulates the radially inner profile of the stator casing of the booster stage of a corresponding type of turbofan engine, and the profile of the inner wall 2 simulates the radially outer profile of the inner ring of the booster stage of a corresponding type of turbofan engine, so as to more accurately simulate the flow channel of the booster stage of the corresponding type of turbofan engine and further improve the accuracy of the test results.

[0055] This anti-icing test method can simultaneously simulate the airflow in the bypass duct and the airflow in the core duct of a turbofan engine, making the gas flow velocities on the upper and lower surfaces of the splitter ring test piece consistent with the actual flow velocities under the established working conditions. Thus, the anti-icing test of the splitter ring can be effectively carried out, ensuring the accuracy of the test results, improving the test efficiency, and then effectively guiding the design of the anti-icing system, shortening the design cycle of the aeroengine, and improving the safety and reliability of the aeroengine.

[0056] Although the present invention is disclosed above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change, and modification made to the above embodiments based on the technical essence of the present invention without departing from the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A flow path simulation component for the anti-icing test of the splitter ring of a turbofan engine, characterized in that, Comprising: An outer wall, which is a rotating body, and the upstream end of the outer wall is used to connect the splitter ring test piece; An inner wall, which is a rotating body and is located radially inside the outer wall; A channel formed between the outer wall and the inner wall for connecting a suction device to simulate the core flow of the compressor of the turbofan engine; And A plurality of support members evenly distributed in the circumferential direction of the outer wall and the inner wall, and both ends of the support members are respectively connected to the outer wall and the inner wall.

2. The runner simulation part according to claim 1, characterized in that, The flow path simulation member further includes a plurality of through holes evenly distributed in the circumferential direction of the flow path simulation member and penetrating the inner wall, the outer wall and the support members, wherein each support member corresponds to at least one through hole.

3. The runner simulation part according to claim 1, characterized in that, The upstream side area of the channel is larger than the downstream side area.

4. The runner simulation part according to claim 1, characterized in that, The support member is an airfoil structure.

5. The runner simulation part according to claim 4, wherein The direction from the leading edge to the trailing edge of the airfoil structure is parallel to the direction from the upstream side to the downstream side of the channel.

6. The flow channel simulation part according to any one of claims 1 to 5, characterized in that The number of the support members is not less than 6 and not more than 10.

7. The runner simulation part according to any one of claims 1 to 5, characterized in that The outer wall and the inner wall are respectively provided with outer mounting holes and inner mounting holes, the outer mounting holes and the inner mounting holes correspond to the cross-sectional shapes of the plurality of support members, and both ends of the support members are respectively inserted into the outer mounting holes and the inner mounting holes and welded to the outer wall and the inner wall respectively.

8. The runner simulation part according to any one of claims 1 to 5, characterized in that, The support member is perpendicular to the outer wall or / and the inner wall.

9. Anti-icing test device, including a first fan, characterized in that, The anti-icing test device further includes a second fan and a flow path simulation member as described in any one of claims 1 to 8. The first fan is used to simulate the bypass flow of the compressor of the turbofan engine, and the second fan is used to provide the suction device. The second fan is connected to the downstream side of the channel.

10. The anti-icing test device according to claim 9, characterized in that, The flow path simulation member further includes a plurality of through holes evenly distributed in the circumferential direction of the flow path simulation member and penetrating the inner wall, the outer wall and the support members, wherein each support member corresponds to at least one through hole. The anti-icing test device further includes a detection element, a test lead and a test bench. The detection element is arranged on the splitter ring test piece, the test lead is communicatively connected to the detection element and the test bench, and the test lead passes through one or more through holes.

11. Anti-icing test method, characterized in that, Using the anti-icing test device as described in claim 9 or 10, design the upstream side area and the downstream side area of the channel according to the maximum suction volume of the second fan and the maximum speed of the core flow required for the test.

12. The anti-icing test method according to claim 11, wherein, The profiles of the outer wall and the inner wall respectively simulate the profiles of the stator casing of the booster stage and the inner ring of the booster stage of the turbofan engine.

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