A shunt ring anti-icing test device, system and test method thereof

Abstract

The application is a kind of diversion ring anti-icing test device, system and test method thereof. The test device comprises: a pressurization stage inner flow channel component, a diversion ring component, a pressurization stage IGV planar cascade component and a bleed air structure, the pressurization stage inner flow channel component and the diversion ring component are fixedly connected through the pressurization stage IGV planar cascade component, the bleed air structure is connected with the diversion ring component, and the pressurization stage inner flow channel component, the diversion ring component and the pressurization stage IGV planar cascade component are respectively a circumferential local part or an expansion of a circumferential local part of a real pressurization stage inner flow channel, a real engine diversion ring and a real pressurization stage IGV cascade. In the test system, the pressurization stage inner flow channel component is fixedly installed on the bottom wall of the icing wind tunnel, the top wall is provided with a hole, the bleed air structure gas conveying section extends out of the hole to introduce hot air. The application also provides the diversion ring anti-icing test method. The application simplifies the full-ring three-dimensional test of the diversion ring into a two-dimensional test, so that the test can be carried out in a small-size icing wind tunnel.

Description

Technical Field

[0001] This invention relates to an anti-icing test device, system, and test method thereof, particularly an anti-icing test device, system, and test method for a shunt ring. Background Technology

[0002] Because clouds may contain metastable supercooled liquid water with temperatures below freezing, icing can easily occur on the surfaces of aircraft's windward components when they pass through these clouds. For aircraft engine components, such as hoods, fan blades, intake manifolds, and engine sensors, the probability of icing is even higher due to the acceleration and cooling of airflow caused by the engine's suction.

[0003] The air splitter ring is typically located after the rotating fan at the engine inlet, separating the inlet airflow into two paths: the outer bypass airflow and the inner bypass airflow. Because the air splitter ring is located at the engine inlet and is a stationary component, its surface is prone to icing during icy weather. Icing on the air splitter ring surface alters its original aerodynamic shape, causing the engine to deviate from its design parameters. Icing also typically causes uneven circumferential blockage of the flow channels, potentially leading to intake distortion or surge. If the icing is severe, detached ice fragments are highly likely to be sucked into the engine's inner cavity and collide with the high-speed rotating engine blades, causing structural damage to the engine.

[0004] Because the shunting ring is susceptible to icing, anti-icing design is necessary, and anti-icing performance tests are required to verify its sufficient anti-icing capability. Anti-icing performance tests necessitate simulating the icing weather conditions encountered by the shunting ring in an ice-cooled wind tunnel or an open-air environment. Currently, the overall engine shunting ring is quite large; the diameter of the shunting ring in a narrow-body passenger aircraft engine is approximately 1 meter, while the diameter in a wide-body passenger aircraft engine is even close to 2 meters. Most ice-cooled wind tunnels worldwide are less than 1 meter in length and width, and only a handful can fully simulate the shunting ring structure. A few ice-cooled wind tunnels are large enough to meet the full-scale testing requirements for narrow-body passenger aircraft engine shunting rings, but not for wide-body passenger aircraft engine shunting rings. Furthermore, the large inner diameter of these ice-cooled wind tunnels requires enormous resources to simulate real icing environments. Therefore, in engine anti-icing performance verification, only whole-engine anti-icing tests are conducted. Verifying that the overall engine anti-icing performance meets the requirements indirectly proves that the shunting ring's anti-icing performance also meets the requirements. However, the icing condition of the shunt ring cannot be observed in the whole-machine anti-icing test, so the anti-icing characteristics of the shunt ring cannot be fully verified through the whole-machine anti-icing test. Summary of the Invention

[0005] The purpose of this invention is to provide a shunt ring anti-icing test device that can simulate the real operating environment of an aero-engine in a small-sized ice wind tunnel for shunt ring anti-icing tests.

[0006] Another object of the present invention is to provide a shunt ring anti-icing test system, which includes an ice wind tunnel and the aforementioned shunt ring anti-icing test device.

[0007] Another objective of this invention is to provide a method for testing the anti-icing of a shunt ring, which simulates the actual operating environment of an aero-engine in a small-sized icing wind tunnel.

[0008] In an optional embodiment, the flow splitter ring anti-icing test device, used for ice wind tunnel testing, includes a booster stage internal flow channel component, a flow splitter ring component, and a booster stage IGV planar blade cascade component. The booster stage internal flow channel component and the flow splitter ring component are fixedly connected through the booster stage IGV planar blade cascade component. The test device also includes an air bleed structure connected to the flow splitter ring component. The booster stage internal flow channel component, the flow splitter ring component, and the booster stage IGV planar blade cascade component are respectively circumferential portions or circumferential portions of a real booster stage internal flow channel, a real engine flow splitter ring, and a real booster stage IGV blade cascade.

[0009] In an optional embodiment, the internal flow channel component of the booster stage is provided with an installation edge for connection to the bottom wall of the ice tunnel by welding or bolting.

[0010] In an optional embodiment, the shunt ring component has an inlet at its rear, which is connected to the air intake structure.

[0011] In an optional embodiment, the air intake structure is divided into an air supply section and an air delivery section. The end of the air supply section connected to the diversion ring component is provided with a protrusion, which is used to connect the diversion ring component in a snap-fit ​​manner.

[0012] In one optional embodiment, the air delivery section and the air conveying section of the air intake structure are connected by an integral molding or a split molding compression connection method.

[0013] In an optional embodiment, the booster stage IGV planar blade assembly is connected to the booster stage inner flow channel assembly by welding or mounting bolts, simulating the installation state of the booster stage IGV blades in the engine.

[0014] In one alternative embodiment, a shunt ring anti-icing test system includes:

[0015] As described above, in the anti-icing test device and ice tunnel of the flow divider ring, the internal flow channel component of the pressurization stage is connected to the bottom wall of the ice tunnel, and the air intake structure extends out from the hole in the top wall of the ice tunnel to introduce hot air to simulate the anti-icing hot air of the flow divider ring.

[0016] In one alternative embodiment, the ice wind tunnel is a rectangular ice wind tunnel.

[0017] In an optional embodiment, a method for testing anti-icing of a shunt ring, used in an ice wind tunnel test, includes the following steps:

[0018] Provides a booster stage internal flow channel component, a flow splitter ring component, and a booster stage IGV planar blade cascade component, which are respectively circumferential partial or circumferential partial unfoldings of the real booster stage internal flow channel, the real engine flow splitter ring, and the real booster stage IGV blade cascade component;

[0019] The internal flow channel components of the booster stage are fixedly connected to the bottom wall of the ice tunnel to simulate the internal flow channel of a real booster stage.

[0020] The planar blade cascade component of the booster stage IGV is connected between the internal flow channel component and the splitter ring component of the booster stage to simulate the installation state of the real booster stage IGV blade in the engine.

[0021] One end of the air intake structure is connected to the diversion ring component, and the other end extends out through the hole in the top wall of the ice wind tunnel to introduce hot air, simulating the anti-icing hot air of a real diversion ring.

[0022] After assembly, an ice cave test was conducted to simulate the actual operating environment of the shunt ring.

[0023] The beneficial effects of this invention are as follows:

[0024] Since the booster stage internal flow channel component, the splitter ring component, and the booster stage IGV planar blade assembly are respectively circumferentially partial or circumferentially partial unfolded components of the actual booster stage internal flow channel, the actual engine splitter ring, and the actual booster stage IGV blade assembly, they can simulate the actual operating environment of the splitter ring without the need for full-ring testing. The reduced size of the test apparatus lowers the weight of the test apparatus, reduces risk, and reduces the resources and costs required for manufacturing the splitter ring test apparatus. It also lowers the requirements for test equipment in the splitter ring anti-icing test, allowing it to be conducted in a small-sized icing wind tunnel, further reducing test costs, saving resources, and shortening test time, while simultaneously meeting the requirements for splitter ring anti-icing performance verification. Attached Figure Description

[0025] The above and other features, properties and advantages of the present invention will become more apparent from the following detailed description of specific embodiments of the invention in conjunction with the accompanying drawings, wherein:

[0026] Figure 1 This is a partial cross-sectional view of a turbofan engine.

[0027] Figure 2 This is a schematic diagram of the internal flow channel components of the booster stage;

[0028] Figure 3 A schematic diagram of a rectangular ice tunnel component;

[0029] Figure 4 A schematic diagram of the internal flow channel components of the booster stage installed in the ice tunnel;

[0030] Figure 5 This is a schematic diagram of the flow divider ring component;

[0031] Figure 6 This is a schematic diagram of the ducting ring air intake structure;

[0032] Figure 7 This is a schematic diagram of the assembly of the flow divider ring component and the bleed air structure;

[0033] Figure 8 A schematic diagram of the planar blade array component of the booster stage IGV;

[0034] Figure 9 This is a schematic diagram of the shunt ring anti-icing test system;

[0035] Figure 10 This is a cross-sectional view of the shunt ring anti-icing test system;

[0036] Figure 11 This is a left view of the shunt ring anti-icing test system.

[0037] Figure label:

[0038] 1-Fan, 2-Low-pressure compressor, 21-Low-pressure compressor outlet, 3-High-pressure compressor, 4-Combustion chamber, 5-High-pressure turbine, 6-Low-pressure turbine, 7-Fan casing, 71-Fan outlet, 72-Split ring, 8-Split ring component, 81-Leading edge annular channel, 82-Inlet gas collection chamber, 83-Inlet gas inlet, 9-Inlet gas structure, 91-Protrusion, 92-Gas delivery section, 93-Gas transport section, 10-Rectangular ice tunnel, 101-Bottom wall, 102-Top wall, 11-Inner flow channel of booster stage, 111-Bottom plate, 112-Flow channel plate, 1120-Inner flow channel surface of booster stage, 12-Inner flow channel component of booster stage IGV planar blade assembly. Detailed Implementation

[0039] Reference will now be made in detail to various embodiments of the invention, examples of which are shown in the accompanying drawings and described below. Although the invention will be described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit the invention to those exemplary embodiments. Rather, the invention is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents, and other embodiments that may be included within the spirit and scope of the invention as defined by the appended claims.

[0040] The following implementation simplifies the three-dimensional test of the shunt ring to a two-dimensional test, allowing anti-icing tests to be conducted in a small-sized icing wind tunnel. This small-sized icing wind tunnel can be, for example, […]. Figure 3The rectangular ice tunnel 10 shown includes a bottom wall 101 and a top wall 102 for mounting the test apparatus. The test apparatus includes a booster stage internal flow channel component 11, a flow splitter ring component 8, a booster stage IGV planar blade assembly 12, and an air bleed structure 9, which are respectively circumferential portions or circumferential portions of the actual booster stage internal flow channel, the actual engine flow splitter ring, and the actual booster stage IGV blade assembly.

[0041] like Figure 1 As shown, a turbofan engine comprises a fan 1, a low-pressure compressor 2, a high-pressure compressor 3, a combustion chamber 4, a high-pressure turbine 5, a low-pressure turbine 6, and a fan casing 7. The high-pressure compressor 3, combustion chamber 4, and high-pressure turbine 5 are collectively referred to as the core engine. The airflow passing through fan 1 is split at the splitter ring 72. A portion of the air enters the low-pressure compressor 2; this portion is called the inner airflow. The majority of the air flows through the outer ring of the core engine casing, called the outer bypass airflow. The inner airflow is compressed by the compressor, mixed with fuel in the combustion chamber, and the combustion gas expands through the turbine and nozzle, exiting at high speed from the exhaust nozzle, generating thrust. Its path is through the low-pressure compressor 2, high-pressure compressor 3, combustion chamber 4, high-pressure turbine 5, and low-pressure turbine 6, finally exiting from the nozzle. The outer bypass airflow of the turbofan engine, after passing through the fan, is either directly discharged into the atmosphere through the outer bypass duct or discharged from the nozzle along with the inner combustion gas. The turbofan engine converts most of the combustion gas energy into torque to drive the fan and compressor, and the remainder into thrust.

[0042] The true boost stage internal flow channel is from Figure 1 The annular surface between the outlet 71 of fan 1 and the outlet 21 of low-pressure compressor 2 is shown. Figure 2 The diagram shows the internal flow channel component 11 of the booster stage. This component simulates the actual internal flow channel of a booster stage and is a linearly expanded, circumferential portion of the real booster stage's internal flow channel. It includes a base plate 111 and a flow channel plate 112. The base plate 111 mounts the booster stage internal flow channel component 11. The upper surface of the flow channel plate 112 provides a booster stage internal flow channel surface 1120. The width of this surface 1120 is the same as the actual internal flow channel after linear expansion, and its length is the same as the actual internal flow channel. The base plate 111 and the flow channel plate 112 are either integrally formed or separately formed and then connected by welding or connectors. The booster stage internal flow channel has a significant impact on the icing of the splitter ring; therefore, by simulating the booster stage internal flow channel, the actual operating environment of the aero-engine's splitter ring can be simulated. The base plate 111 has mounting edges and can be fixedly connected by welding or bolts, allowing the internal flow channel component to be mounted as described above. Figure 4 It is fixedly connected to the bottom wall 101 of the ice wind tunnel.

[0043] The actual shunt ring 72 is located in Figure 1 The annular structure at the outlet 71 of fan 1, where the internal and external airflows diverge. (See diagram.) Figure 5 The diagram shows the flow splitter ring component 8. Flow splitter ring component 8 is used to simulate a real flow splitter ring component. It is a linear unfolded portion of the real flow splitter ring in the circumferential direction. Its width is the same as the actual flow splitter ring after unfolding in the circumferential linear direction, and its length is the same as the actual flow splitter ring. The front part of the flow splitter ring component 8 includes a leading edge 81, which is an anti-icing structure, simulating the anti-icing structure of a real flow splitter ring; its interior is a hollow inlet air collecting chamber 82, simulating the air collecting chamber of a real aircraft engine; its rear part has an air vent 83, connected to... Figure 6 The bleed air structure 9 is shown. The splitter ring component 8 can simulate the complete splitter ring structure of an engine, and the test can be completed without the need for a large full-size splitter ring, reducing the resources and costs required to process the splitter ring test piece.

[0044] The actual booster stage IGV blades are located in Figure 1 The first fixed blade at the inlet of the low-pressure compressor 2 is shown. Figure 8 The turbocharger stage IGV planar blade assembly 12 shown is constructed using real engine blades to form a planar blade structure. The splitter ring assembly 8 and the turbocharger stage inner flow channel assembly 11 are fixedly connected by welding or mounting bolts to simulate the installation state of real turbocharger stage IGV blades in the engine.

[0045] In other optional embodiments of the present invention, the structure and dimensions of the booster stage internal flow channel component 11, the flow splitter ring component 8, and the booster stage IGV planar blade cascade component 12 can be determined according to the shape and dimensions of the ice wind tunnel used in the experiment. The booster stage internal flow channel component 11, the flow splitter ring component 8, and the booster stage IGV planar blade cascade component 12 are not limited to linear expansions of the actual booster stage internal flow channel, the actual flow splitter ring, and the actual booster stage IGV blade cascade in a circumferential local form. They can also be expansions of the actual booster stage internal flow channel, the actual flow splitter ring, and the actual booster stage IGV blade cascade in a circumferential local form or other forms of circumferential local expansion.

[0046] like Figure 6 The air intake structure 9 shown is divided into an air supply section 92 and an air delivery section 93, which can be flat tubular. The air supply section 92 and the air delivery section 93 can be vertically connected. They can be integrally formed or separately formed and tightly connected by a snap-fit ​​connection method. The end of the air supply section 92 connected to the diversion ring component has a protrusion 91. The outer edge of the protrusion 91 is larger than the size of the air intake port 83, and the diversion ring component can be connected by a snap-fit ​​method. The top wall 102 of the ice wind tunnel has a hole that matches the size of the air delivery section 93, through which the air delivery section 93 extends out. Figure 7 As shown, hot air is introduced through the air intake structure 9 and enters the split ring component 8 through the air intake port 83, simulating the anti-icing hot air of the real split ring. This can effectively reduce the amount of air required for the anti-icing test of the split ring and reduce energy consumption.

[0047] After all the above test structures are assembled, they form the following structure: Figure 9 The test system shown includes the aforementioned anti-icing test device for the splitter ring and the ice wind tunnel, which can simulate the actual operating environment of the engine splitter ring.

[0048] This invention also provides a method for conducting an anti-icing test on a splitter ring, comprising the following steps: providing a booster stage internal flow channel component 11, a splitter ring component 8, and a booster stage IGV planar blade assembly 12, which are respectively circumferential portions or circumferential portions of a real booster stage internal flow channel, a real engine splitter ring, and a real booster stage IGV blade assembly. Next, the booster stage internal flow channel component 11 is fixedly connected to the bottom wall 101 of an ice tunnel, and the booster stage IGV planar blade assembly 12 is connected between the booster stage internal flow channel component 11 and the splitter ring component 8. One end of an air bleed structure 9 is connected to the splitter ring component, and the other end extends out through a hole in the top wall of the ice tunnel to introduce hot air. After assembly, an ice tunnel test is conducted, simulating the operating environment of the splitter ring. Using this method eliminates the need for full-ring testing, reducing costs and testing time.

[0049] While the structure and working principle of the present invention have been described above with reference to preferred embodiments, those skilled in the art should recognize that the above examples are merely illustrative and should not be construed as limiting the invention. Therefore, modifications and variations can be made to the invention within the spirit and scope of the claims, and all such modifications and variations will fall within the scope claimed by the claims.

Claims

1. A flow divider ring anti-icing test device for use in ice wind tunnel tests, characterized in that, The test apparatus includes a booster stage internal flow channel component, a flow splitter ring component, and a booster stage IGV planar blade assembly. The booster stage internal flow channel component and the flow splitter ring component are fixedly connected through the booster stage IGV planar blade assembly. The test apparatus also includes an air bleed structure connected to the flow splitter ring component. The booster stage internal flow channel component, the flow splitter ring component, and the booster stage IGV planar blade assembly are respectively circumferential portions or circumferential portions of a real booster stage internal flow channel, a real engine flow splitter ring, and a real booster stage IGV blade assembly.

2. The anti-icing test device for the diversion ring according to claim 1, characterized in that, The booster stage internal flow channel component is provided with an installation edge for connection to the bottom wall of the ice tunnel by welding or bolting.

3. The anti-icing test device for the diversion ring according to claim 1, characterized in that, The shunt ring component has an air intake port at the rear, which is connected to the air intake structure.

4. The anti-icing test device for the diversion ring according to claim 1, characterized in that, The air intake structure is divided into an air supply section and an air delivery section. The end of the air supply section that connects to the diversion ring component has a protrusion that connects to the diversion ring component in a snap-fit ​​manner.

5. The anti-icing test device for the diversion ring according to claim 4, characterized in that, The air delivery section and the air conveying section of the air intake structure are connected by an integral molding or a split molding compression connection method.

6. The anti-icing test device for the diversion ring according to claim 1, characterized in that, The booster stage IGV planar blade assembly is connected to the booster stage inner flow channel assembly by welding or mounting bolts, simulating the installation state of the booster stage IGV blades in the engine.

7. A shunt ring anti-icing test system, characterized in that, The device includes the anti-icing test apparatus for the split ring and the ice wind tunnel according to any one of claims 1-6, wherein the internal flow channel component of the pressurization stage is connected to the bottom wall of the ice wind tunnel, and the air intake structure extends out from the hole in the top wall of the ice wind tunnel to introduce hot air to simulate the anti-icing hot air of the split ring.

8. The shunt ring anti-icing test system according to claim 7, characterized in that, The ice cave is a rectangular ice cave.

9. A method for testing anti-icing of a shunt ring, used in an ice wind tunnel test, characterized in that, The method includes the following steps: Provides a booster stage internal flow channel component, a flow splitter ring component, and a booster stage IGV planar blade cascade component, which are respectively circumferential partial or circumferential partial unfolded parts of the real booster stage internal flow channel, the real engine flow splitter ring, and the real booster stage IGV blade cascade component; The internal flow channel components of the booster stage are fixedly connected to the bottom wall of the ice tunnel to simulate the internal flow channel of a real booster stage. The planar blade cascade component of the booster stage IGV is connected between the internal flow channel component and the splitter ring component of the booster stage to simulate the installation state of the real booster stage IGV blade in the engine. One end of the air intake structure is connected to the diversion ring component, and the other end extends out through the hole in the top wall of the ice wind tunnel to introduce hot air, simulating the anti-icing hot air of a real diversion ring. After assembly, an ice cave test was conducted to simulate the actual operating environment of the shunt ring.

Images