Aero-engine fan radar wave-absorbing structure

Abstract

The application relates to an aero-engine fan radar wave-absorbing structure, which comprises a support casing, a rear end of which is connected with a front end of an air inlet casing, and a plurality of strip-shaped guide holes are arranged on the support casing in a circumferential direction; a support ring is arranged in the support casing; a plurality of hollow support plates are arranged between the support casing and the support ring in a circumferential direction, the upper ends of the hollow support plates are open and communicated with the strip-shaped guide holes, and the front ends of the hollow support plates are open; a plurality of metal support plates are arranged in the hollow support plates, the metal support plates are provided with grooves on two sides and hinged joints on the upper ends; the hinged joints of the metal support plates are extended out of the support casing from the strip-shaped guide holes; a plurality of pairs of radar wave-absorbing plates are made of radar wave-absorbing materials and are bonded in the grooves on the two sides of the metal support plates; and a linkage ring is sleeved on the outer periphery of the support casing, is hinged with the hinged joints through an ear piece structure and a pin shaft and can move along the axial direction of the support casing, so that the metal support plates and the radar wave-absorbing plates in the grooves on the two sides of the metal support plates can be extended out of or retracted into the hollow support plates through the hinged joints.

Description

Technical Field

[0001] This application belongs to the field of stealth design technology for aircraft engine fan radar, and specifically relates to an aircraft engine fan radar absorbing structure. Background Technology

[0002] The fan, located at the front of the aero-engine's air intake, has a significant impact on the engine's radar stealth performance. To improve the fan's radar stealth performance and thus ensure the engine's overall radar stealth performance, current designs often employ radar-absorbing coatings or radar-absorbing structures. However, this approach has the following drawbacks:

[0003] Radar absorbing coatings and structures are constantly exposed to the strong scouring of airflow throughout the entire life cycle of an aero-engine. Especially during the takeoff phase of an aircraft when radar stealth is not required, the scouring force of the airflow is high and there is a lot of sand and dust in the airflow, which can easily damage the radar absorbing coatings and structures, greatly shortening their effective service life and thus limiting the service life of the aero-engine.

[0004] This application is made in view of the aforementioned technical deficiencies.

[0005] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this application, and it does not necessarily belong to the prior art of this application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0006] The purpose of this application is to provide a radar absorbing structure for an aircraft engine fan to overcome or mitigate at least one of the known technical defects.

[0007] The technical solution of this application is:

[0008] A radar-absorbing structure for an aircraft engine fan includes:

[0009] The supporting casing has a rear end that connects to the front end of the intake casing, and has multiple circumferentially distributed strip-shaped guide holes.

[0010] The support ring is installed inside the support housing;

[0011] Multiple hollow support plates are circumferentially supported between the support casing and the support ring, with the upper end open and connected to each strip guide hole, and the front end open;

[0012] Multiple metal support plates are installed in each hollow support plate, with grooves on both sides and hinge joints at the top; each hinge joint extends out of each strip guide hole to the outside of the support casing;

[0013] Multiple pairs of radar absorbing plates, made of radar absorbing material, are bonded to the grooves on both sides of each metal support plate, flush with the surface of both sides of the metal support plate.

[0014] The linkage ring is sleeved on the outer periphery of the support casing. It is hinged to each hinge joint by a pin through an ear structure. It can move along the axial direction of the support casing. In this way, it can drive the metal support plate and the radar absorbing plate in the grooves on both sides to extend or retract from the hollow support plate through each hinge joint.

[0015] According to at least one embodiment of this application, in the above-mentioned aircraft engine fan radar absorbing structure, when each metal support plate retracts into the hollow support plate, the leading edge is located outside the hollow support plate, the cross-section is conical, it has an anti-icing air passage inside, and there is a smooth transition between it and the surface of the hollow support plate.

[0016] The support casing has multiple front anti-icing vents and rear anti-icing vents distributed circumferentially.

[0017] When each metal support plate retracts into the hollow support plate, each anti-icing vent is connected to each rear anti-icing vent.

[0018] When each metal support plate extends out of the hollow support plate, each anti-icing vent is connected to each front anti-icing vent.

[0019] The radar absorbing structure for the aircraft engine fan also includes:

[0020] The front anti-icing air duct ring is fitted onto the support casing, forming a front anti-icing air duct chamber that communicates with each front anti-icing vent hole and is connected to the anti-icing air source through a pipeline.

[0021] The rear anti-icing air duct ring is fitted onto the support casing, forming a rear anti-icing air duct chamber that communicates with each rear anti-icing vent hole and is connected to the anti-icing air source through a pipeline.

[0022] According to at least one embodiment of this application, the above-described aircraft engine fan radar absorbing structure further includes:

[0023] The cap is cone-shaped and connected to the front end of the support ring.

[0024] According to at least one embodiment of this application, the above-described aircraft engine fan radar absorbing structure further includes:

[0025] The actuator is connected between the support housing and the linkage ring to drive the linkage ring to move axially along the support housing. Attached Figure Description

[0026] Figure 1This is a schematic diagram of the radar absorbing structure for an aero-engine fan provided in an embodiment of this application;

[0027] Figure 2 Figure 1 A partial schematic diagram;

[0028] Figure 3 This is a schematic diagram of the assembly of the metal support plate and the radar absorbing plate provided in the embodiments of this application;

[0029] Figure 4 This is a schematic diagram of the linkage ring of the radar absorbing structure of the aero-engine fan provided in this application, which drives the metal support plate to retract into the hollow support plate;

[0030] Figure 5 This is a schematic diagram of the linkage ring of the radar absorbing structure of the aero-engine fan provided in this application, which drives the metal support plate to extend out from the hollow support plate;

[0031] in:

[0032] 1-Support casing; 2-Intake casing; 3-Support ring; 4-Hollow support plate; 5-Metal support plate; 6-Radar absorber plate; 7-Linkage ring; 8-Front anti-icing air bleed ring; 9-Rear anti-icing air bleed ring; 10-Cap cover.

[0033] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. Detailed Implementation

[0034] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0035] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0036] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0037] The following is in conjunction with the appendix Figures 1 to 5 This application will be described in further detail.

[0038] A radar-absorbing structure for an aircraft engine fan, such as Figure 1 As shown, it includes:

[0039] The support casing 1 is connected at the rear end to the front end of the intake casing 2 and is located in front of the fan. It has multiple strip-shaped guide holes distributed along the circumference.

[0040] The support ring 3 is installed inside the support housing 1;

[0041] Multiple hollow support plates 4 are circumferentially supported between the support casing 1 and the support ring 3, with the upper end open and connected to each strip guide hole, and the front end open;

[0042] Multiple metal support plates 5 are provided in each hollow support plate 4, with grooves on both sides and hinge joints at the top; each hinge joint extends out of each strip guide hole to the outside of the support casing.

[0043] Multiple pairs of radar-absorbing plates 6, made of radar-absorbing material (which can be composite material), are bonded to the grooves on both sides of each metal support plate 5. Supported by the metal support plates 5, they ensure strength and are flush with the surfaces of both sides of the metal support plates 5. Figure 3 As shown;

[0044] The linkage ring 7 is sleeved on the outer periphery of the support casing 1. It is hinged to each hinge joint by a pin through the lug structure. It can move along the axial direction of the support casing 1. In this way, it can drive the metal support plate 5 and the radar absorbing plate 6 in the grooves on both sides to extend or retract from the hollow support plate 4 through each hinge joint.

[0045] The radar-absorbing structure for an aero-engine fan disclosed in the above embodiments, in specific applications, when the aero-engine requires radar stealth, can drive the linkage ring 7 to drive each metal support plate 5 to extend from the hollow support plate 4, such as... Figure 5 As shown, radar-absorbing plates 6 on both sides of each metal support plate 5 extend simultaneously from the hollow support plate 4 and are exposed in the support casing 1. These plates absorb radar waves, thereby improving the radar stealth performance of the fan and ensuring the radar stealth performance of the aero-engine. Each pair of radar-absorbing plates 6 is embedded in the grooves on both sides of the metal support plate 5, ensuring reliable connection and flush with the surfaces of the metal support plate 5. This protects the edges from strong airflow erosion, extending service life. When radar stealth is not required for the aero-engine, the metal support plates 5 can be retracted into the hollow support plate 4 via the drive linkage ring 7. Figure 4 As shown, the radar absorbing plates 6 on both sides of each metal support plate 5 retract into the hollow support plate 4. Protected by the hollow support plate 4, they are protected from the strong scouring of the airflow and the damage caused by sand and dust, thus effectively extending their service life.

[0046] In some optional embodiments, in the above-mentioned aircraft engine fan radar absorbing structure, when each metal support plate 5 retracts into the hollow support plate 4, its leading edge is located outside the hollow support plate 4, its cross-section is conical, and it smoothly transitions with the surface of the hollow support plate 4 to ensure aerodynamic performance and improve radar stealth performance. Each metal support plate 5 has an anti-icing air passage inside its leading edge.

[0047] The support casing 1 has multiple front anti-icing vents and rear anti-icing vents distributed circumferentially.

[0048] When each metal support plate 5 retracts into the hollow support plate 4, each anti-icing vent is connected to each rear anti-icing vent.

[0049] When each metal support plate 5 extends out of the hollow support plate 4, each anti-icing vent is connected to each front anti-icing vent.

[0050] The radar absorbing structure for the aircraft engine fan also includes:

[0051] The front anti-icing air duct ring 8 is sleeved on the support casing 1, forming a front anti-icing air duct cavity that communicates with each front anti-icing vent hole between the ring and the support casing 1. It is connected to the anti-icing air source through a pipeline, so that when each metal support plate 5 extends out of the hollow support plate 4, anti-icing air can be introduced into the anti-icing vent duct at the front edge of each metal support plate 5 for anti-icing.

[0052] The rear anti-icing air duct ring 9 is fitted onto the support casing 1, forming a rear anti-icing air duct cavity that communicates with each rear anti-icing vent hole. It is connected to the anti-icing air source through a pipeline, so that when each metal support plate 5 is retracted into the hollow support plate 4, anti-icing air can be introduced into the anti-icing vent duct at the front edge of each metal support plate 5 for anti-icing.

[0053] In some optional embodiments, the aforementioned aircraft engine fan radar absorbing structure further includes:

[0054] The cap 10 is conical and connected to the front end of the support ring 3 to avoid radar wave reflection and enhance radar stealth effect.

[0055] In some optional embodiments, the aforementioned aircraft engine fan radar absorbing structure further includes:

[0056] The actuator is connected between the support housing 1 and the linkage ring 7, so as to drive the linkage ring 7 to move along the axial direction of the support housing 1 and to be connected to the control system of the aero engine for control.

[0057] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0058] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the protection scope of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the protection scope of this application.

Claims

1. A radar absorbing structure for an aircraft engine fan, characterized in that, include: The support casing (1) has its rear end connected to the front end of the intake casing (2), and has multiple strip-shaped guide holes distributed circumferentially. A support ring (3) is provided inside the support housing (1); Multiple hollow support plates (4) are circumferentially supported between the support casing (1) and the support ring (3), with the upper end open and connected to each strip guide hole, and the front end open; Multiple metal support plates (5) are provided in each hollow support plate (4), with grooves on both sides and hinge joints at the top; each hinge joint extends out of each strip guide hole to the outside of the support casing. Multiple pairs of radar absorbing plates (6), made of radar absorbing material, are bonded to the grooves on both sides of each metal support plate (5) and are flush with the surface of both sides of the metal support plate (5). The linkage ring (7) is sleeved on the outer periphery of the support casing (1). It is hinged to each hinge joint by a pin through the lug structure. It can move along the axial direction of the support casing (1). In this way, it can drive the metal support plate (5) and the radar absorbing plate (6) in the grooves on both sides to extend or retract from the hollow support plate (4) through each hinge joint.

2. The radar absorbing structure for an aero-engine fan according to claim 1, characterized in that, When each metal support plate (5) retracts into the hollow support plate (4), its leading edge is outside the hollow support plate (4), its cross-section is conical, it has an anti-icing ventilation channel inside, and it has a smooth transition with the surface of the hollow support plate (4). The support casing (1) has multiple front anti-icing vents and rear anti-icing vents distributed along the circumference; When each metal support plate (5) retracts into the hollow support plate (4), each anti-icing vent is connected to each rear anti-icing vent. When each metal support plate (5) extends out from the hollow support plate (4), each anti-icing vent is connected to each front anti-icing vent. The radar absorbing structure for the aircraft engine fan also includes: The front anti-icing air duct ring (8) is fitted onto the support casing (1) and forms a front anti-icing air duct that communicates with each front anti-icing vent hole between it and the support casing (1), and is connected to the anti-icing air source through a pipeline. The rear anti-icing air duct ring (9) is fitted onto the support casing (1) and forms a rear anti-icing air duct chamber that communicates with each rear anti-icing vent hole between it and the support casing (1), and is connected to the anti-icing air source through a pipeline.

3. The radar absorbing structure for an aero-engine fan according to claim 1, characterized in that, Also includes: The cap (10) is conical and connected to the front end of the support ring (3).

4. The radar absorbing structure for an aero-engine fan according to claim 1, characterized in that, Also includes: The actuator is connected between the support housing (1) and the linkage ring (7) so as to drive the linkage ring (7) to move axially along the support housing (1).

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