Casing assembly with containing capacity and engine

Abstract

The invention provides a cartridge receiver assembly with containing capacity and an engine. The cartridge receiver assembly comprises a cartridge receiver and a containing part, the stator blades are arranged in an inner cavity of the casing, the stator blades are provided with a plurality of stator blade rings in the circumferential direction of the casing assembly, the stator blade rings are arranged in the axial direction of the casing assembly, a rotor blade ring is arranged between every two adjacent stator blade rings, and each rotor blade ring comprises a plurality of rotor blades arranged in the circumferential direction of the rotor blade ring; the honeycomb structure is arranged on the periphery of the casing, and at least part of the honeycomb structure corresponds to the rotor blades in the radial direction. Thus, if the engine is abnormal in the operation process and the rotor blades fly off due to factors such as breakage, the fly-off rotor blades impact the positions, provided with the honeycomb structures, of the casing, the honeycomb structures can absorb a large amount of energy generated when the rotor blades fly off, and the containing capacity of the casing assembly is greatly improved; rotor blades are prevented from flying out of the casing, the safety performance of the engine is improved, and flight safety is guaranteed.

Description

Technical Field

[0001] This invention relates to the field of aero engines, and more specifically to a housing assembly and an engine with containment capabilities. Background Technology

[0002] An aircraft engine is a highly complex and precise thermodynamic machine. As the heart of an aircraft, it not only powers the aircraft's flight but also serves as a crucial driving force for the development of the aviation industry. Every major transformation in the history of human aviation has been inseparable from the technological advancements in aircraft engines.

[0003] The related technology has a problem with insufficient containment capacity of the casing, which in extreme cases can cause rotor blades to fly out of the casing, affecting the engine's safety performance. Summary of the Invention

[0004] The present invention was made to solve the above-mentioned technical problems, and its purpose is to provide a housing assembly and engine with containment capacity, which can improve the containment capacity of the housing.

[0005] Firstly, this application discloses a housing assembly with containment capacity, comprising: a housing; stator blades disposed within the inner cavity of the housing, the stator blades having multiple stator blade rings disposed circumferentially along the housing assembly, the stator blade rings having multiple stator blade rings disposed axially along the housing assembly, and rotor blade rings disposed between adjacent stator blade rings, the rotor blade rings comprising multiple rotor blades disposed circumferentially; and a honeycomb structure disposed on the periphery of the housing, at least a portion of the honeycomb structure corresponding to the rotor blades radially. Thus, if an abnormality occurs during engine operation, causing rotor blades to detach due to breakage or other factors, the detached rotor blades will impact the location of the housing with the honeycomb structure. The honeycomb structure can absorb a large amount of the energy from the detached rotor blades, greatly enhancing the containment capacity of the housing assembly, preventing rotor blades from flying out of the housing, improving engine safety performance, and ensuring flight safety.

[0006] Optionally, the honeycomb structure is offset from the stator blade along the radial direction. This, in a first aspect, saves material for the honeycomb structure, reducing material costs; and in a second aspect, it also reduces the space required to house the honeycomb structure, improving the compactness of the casing assembly.

[0007] Optionally, a portion of the honeycomb structure corresponds radially to the gap between the stator blade and the rotor blade, while another portion corresponds radially to the rotor blade. This, on the one hand, can cover as much as possible the area where the rotor blade might impact the casing during flyaway, improving safety performance; on the other hand, it avoids material waste caused by placing the honeycomb structure at the corresponding position on the stator blade.

[0008] Optionally, the honeycomb structure is positioned corresponding to the rotor blades of the first stage, which are the rotor blades closest to the fan disc mounting side among multiple rotor blade rings. During operation, the rotor blades of the first stage are most prone to fly-off, and the kinetic energy generated during fly-off is relatively large. Therefore, the honeycomb structure is positioned at this location to provide reliable safety assurance.

[0009] Optionally, the casing includes an inner wall and an outer wall. The inner wall forms an inner cavity in which the stator blades are disposed, and the outer wall surrounds the inner wall and, together with the inner wall, forms a receiving cavity, in which the honeycomb structure is disposed. In this way, firstly, the casing wall forms a hollow structure, facilitating the placement of the honeycomb structure and improving structural compactness; secondly, it provides a protective shield for the honeycomb structure; and thirdly, it achieves structural lightweighting.

[0010] Optionally, a first positioning rib is formed on the surface of the inner wall facing the receiving cavity. The first positioning ribs are arranged in pairs along the axial direction. One of the paired first positioning ribs is positioned radially to correspond to the gap between the stator blade and the rotor blade, and the other is positioned radially to correspond to the rotor blade. A mounting groove for accommodating the honeycomb structure is formed between the paired first positioning ribs. This arrangement has several advantages: first, it improves the structural strength of the inner wall, thereby improving the structural strength of the casing; second, it facilitates the rapid installation of the honeycomb structure while maintaining the accuracy of its relative position to the rotor blade; and third, the paired first positioning ribs limit the width of the honeycomb structure, avoiding material waste.

[0011] Optionally, multiple honeycomb structures are arranged along the axial direction, and multiple pairs of first positioning ribs are arranged along the axial direction. Each of the multiple honeycomb structures corresponds to a rotor blade on the same rotor blade ring to ensure the containment effect of the detached blade; furthermore, the arrangement of multiple pairs of first positioning ribs can further improve the structural strength of the casing.

[0012] Optionally, the honeycomb structure is fitted to the inner wall and spaced apart from the outer wall. This facilitates airflow within the accommodating cavity, thereby facilitating the introduction of high-temperature airflow from the rear to the front stator blades for cooling.

[0013] Optionally, the stator blades are made of aluminum-based composite materials. Using aluminum-based composite materials in this application, to combine the honeycomb structure with the aluminum-based composite stator blades, can significantly reduce the weight of the casing assembly, thereby improving the engine's thrust-to-weight ratio.

[0014] Optionally, the honeycomb structure includes a honeycomb layer, a satin fabric layer, and a resin base layer; multiple layers of the satin fabric are laid on both opposite end faces of the honeycomb layer, and a resin base layer is disposed between adjacent satin fabric layers. This results in a robust and resilient composite material, thereby protecting the honeycomb layer.

[0015] Secondly, this application discloses an engine, comprising: a casing assembly; and a rotor blade ring disposed between adjacent stationary blade rings. The rotor blade ring includes a plurality of rotor blades arranged circumferentially along the casing assembly, and at least a portion of the honeycomb structure corresponds to the rotor blades radially. This absorbs the energy of the detached rotor blades when an abnormality occurs, preventing the rotor blades from flying out of the casing and ensuring the engine's safety performance.

[0016] The beneficial effects of this invention are as follows:

[0017] This application discloses a housing assembly with containment capacity, comprising: a housing; stator blades disposed within the inner cavity of the housing, wherein multiple stator blade rings are disposed circumferentially along the housing assembly, and multiple stator blade rings are disposed axially along the housing assembly, with rotor blade rings disposed between adjacent stator blade rings, each rotor blade ring comprising multiple rotor blades disposed circumferentially; and a honeycomb structure disposed on the periphery of the housing, at least a portion of the honeycomb structure corresponding radially to the rotor blades. Thus, if an engine malfunctions during operation, causing rotor blades to break or detach, the detached rotor blades will impact the location of the honeycomb structure in the housing. The honeycomb structure can absorb a large amount of the energy from the detached rotor blades, greatly enhancing the containment capacity of the housing assembly, preventing rotor blades from flying out of the housing, improving engine safety performance, and ensuring flight safety. Attached Figure Description

[0018] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related characteristics or features may have the same or similar reference numerals.

[0019] Figure 1 This is an internal structural diagram of the casing assembly of the present invention;

[0020] Figure 2 This is the honeycomb structure of the present invention;

[0021] Figure 3 This is a structural diagram of the engine of the present invention.

[0022] Explanation of reference numerals in the attached figures:

[0023] X-axis, Y-radial,

[0024] 10- Casing assembly,

[0025] 110-Casing, 111-Inner wall, 112-Outer wall, 113-Accommodation cavity, 114-First positioning rib

[0026] 120-Stationary blade,

[0027] 130-Honeycomb structure, 131-Honeycomb layer, 132-Satin fabric layer, 133-Resin base layer,

[0028] 200-Rotor blades. Detailed Implementation

[0029] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention can obviously be implemented in many other ways different from those described herein. Those skilled in the art can make similar extensions and derivations based on actual application situations without departing from the spirit of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific embodiment.

[0030] It should be noted that these and other accompanying drawings are merely examples and are not drawn to scale, and should not be construed as limiting the scope of protection of the present invention.

[0031] An aero-engine is a highly complex and precise thermodynamic machine. As the heart of an aircraft, it not only powers flight but also serves as a crucial driving force for the development of aviation. Every significant revolution in human aviation history is inextricably linked to advancements in aero-engine technology. However, some related technologies suffer from insufficient containment capacity in the engine casing, which, in extreme cases, can cause rotor blades to fly out of the casing, affecting engine safety. Therefore, this application's technical solution was developed. The following section combines... Figures 1-3 To elaborate.

[0032] This application discloses a housing assembly 10 with containment capability. The housing assembly 10 can be a supercharger housing assembly of an engine, located behind the fan disk 30. The housing assembly 10 includes a housing 110, stator blades 120, and a honeycomb structure 130.

[0033] The casing 110 provides a mounting base and protective shield for the relevant components of the casing assembly 10 of this application. The stator blades 120 are disposed in the inner cavity of the casing 110. The stator blades 120 are arranged with multiple stator blade rings along the circumference of the casing assembly 10, and multiple stator blade rings are arranged along the axial direction X of the casing assembly 10. Rotor blade rings are arranged between adjacent stator blade rings. The rotor blade rings include multiple rotor blades 200 arranged along their own circumference. Thus, in the engine, multiple stator blade rings and rotor blade rings are alternately arranged along the axial direction X. During operation, the stator blades 120 remain stationary in their circumferential position and provide airflow guidance, while the rotor blades 200 are driven to rotate at high speed by the engine shaft. The air is accelerated when passing through the high-speed rotating rotor blades 200.

[0034] A honeycomb structure 130 is disposed around the periphery of the casing 110, and at least a portion of the honeycomb structure 130 corresponds to the rotor blade 200 along the radial direction Y. The honeycomb structure 130 has a honeycomb layer 131, and the honeycomb structure 130 is generally an annular structure that covers the periphery of the casing 110 in the circumferential direction.

[0035] Thus, if an abnormality occurs during engine operation, causing the rotor blade 200 to break or detach, the detached rotor blade 200 will impact the location of the honeycomb structure 130 in the casing 110. The honeycomb structure 130 can absorb a large amount of the energy from the detached rotor blade 200, greatly enhancing the containment capacity of the casing assembly 10, preventing the rotor blade 200 from flying out of the casing 110, improving engine safety performance, and ensuring flight safety.

[0036] Optionally, as described above, since the stator blade 120 is fixed circumferentially, it will not detach or experience other abnormalities. Therefore, the honeycomb structure 130 can be offset from the stator blade 120 along the radial direction Y. This saves material for the honeycomb structure 130 and reduces material costs. Furthermore, it reduces the space required to house the honeycomb structure 130, improving the compactness of the casing assembly 10.

[0037] Optionally, a portion of the honeycomb structure 130 corresponds along the radial direction Y to the gap between the stator blade 120 and the rotor blade 200, and another portion corresponds along the radial direction Y to the rotor blade 200. This, on the one hand, can cover as much as possible the position where the rotor blade 200 might impact the casing 110 when it detaches, improving safety performance; on the other hand, it avoids material waste caused by placing the honeycomb structure 130 at the corresponding position of the stator blade 120.

[0038] Optionally, the honeycomb structure 130 is positioned corresponding to the first-stage rotor blade 200, which is the rotor blade 200 closest to the fan disc 30 mounting side among multiple rotor blade rings. During operation, the first-stage rotor blade 200 is most prone to detachment, and the kinetic energy generated during detachment is relatively large. Therefore, positioning the honeycomb structure 130 at this location provides reliable safety assurance.

[0039] Optionally, the casing 110 includes an inner wall 111 and an outer wall 112. The inner wall 111 forms the inner cavity in which the stator blade 120 is disposed, and the outer wall 112 surrounds the inner wall 111 and together with the inner wall 111 forms a receiving cavity 113, in which the honeycomb structure 130 is disposed. Thus, in a first aspect, the casing of the casing 110 forms a hollow structure, facilitating the placement of the honeycomb structure 130 and improving structural compactness; in a second aspect, it provides a protective shield for the honeycomb structure 130; and in a third aspect, it achieves structural lightweighting.

[0040] Optionally, the inner wall 111 and the outer wall 112 are a combined structure. During assembly, the honeycomb structure 130 is first set on the inner wall 111, and then the outer wall 112 is installed, which facilitates assembly and manufacturing.

[0041] Optionally, a first positioning rib 114 is formed on the surface of the inner wall 111 facing the receiving cavity 113. The first positioning rib 114 is an annular rib protruding circumferentially along the inner wall 111. The first positioning ribs 114 are arranged in pairs along the axial direction X. In the pair of first positioning ribs 114, one of them is positioned along the radial direction Y to correspond to the gap between adjacent stator blades 120 and rotor blades 200, and the other is positioned along the radial direction Y to correspond to the rotor blades 200. A mounting groove for accommodating the honeycomb structure 130 is formed between the pairs of first positioning ribs 114. The mounting groove is an annular groove formed circumferentially along the inner wall 111.

[0042] This arrangement has several advantages. First, it can improve the structural strength of the inner wall 111 and thus the structural strength of the casing 110 by setting the first positioning rib 114. Second, it facilitates the quick installation of the honeycomb structure 130 and maintains the accuracy of its relative position with the rotor blades 200. Third, the paired first positioning ribs 114 can limit the width of the honeycomb structure 130 and avoid material waste.

[0043] Optionally, a second positioning rib 115 is formed on the surface of the outer wall 112 facing the receiving cavity 113. At least a portion of the second positioning rib 115 and the first positioning rib 114 are in contact with each other along the axial direction X. This facilitates the installation and positioning of the outer wall 112 and ensures the structural strength of the outer wall 112, thereby ensuring the structural strength of the casing 110.

[0044] Optionally, multiple honeycomb structures 130 are provided along the axial direction X, and multiple pairs of first positioning ribs 114 are provided along the axial direction X. Each of the multiple honeycomb structures 130 corresponds to a rotor blade 200 on the same rotor blade ring to ensure the containment effect of the detached blade; and the provision of multiple pairs of first positioning ribs 114 can further improve the structural strength of the casing 110.

[0045] Optionally, the honeycomb structure 130 is fitted to the inner wall 111 and spaced apart from the outer wall 112, which facilitates airflow in the accommodating cavity 113 and facilitates the introduction of high-temperature airflow from the rear to the stator blade 120 at the front for cooling.

[0046] Optionally, the stator blade 120 is an aluminum-based composite material. Aluminum-based composite materials are a powerful material that has emerged in response to the needs of modern scientific development. They are composed of two or more materials with different properties through various processing methods. Aluminum-based composite materials can be divided into three categories: polymer composites (PMCs), metal matrix composites (MMCs), and ceramic matrix composites (CMCs). The matrix of metal matrix composites is mainly aluminum, nickel, magnesium, titanium, etc. Aluminum has many advantages in the manufacture of composite materials, such as light weight, low density, good plasticity, easy mastery of aluminum-based composite technology, and ease of processing. In addition, aluminum-based composite materials have high specific strength and specific stiffness, good high-temperature performance, better fatigue and wear resistance, good damping performance, and a low coefficient of thermal expansion.

[0047] The application of aluminum-based composite materials in this application, so that the honeycomb structure 130 and the aluminum-based composite stator blades 120 can be matched, can also greatly reduce the mass of the casing assembly 10, thereby improving the thrust-to-weight ratio of the engine.

[0048] Optionally, the honeycomb structure 130 includes a honeycomb layer 131, a satin fabric layer 132, and a resin base layer 133. Multiple layers of the satin fabric layer 132 are laid on both opposite end faces of the honeycomb layer 131, and a resin base layer 133 is disposed between adjacent satin fabric layers 132. The surface of the honeycomb layer 131 is covered with the satin fabric layer 132 and the resin base layer 133 to prevent internal defects from occurring in the honeycomb structure 130.

[0049] Furthermore, the satin fabric layer 132 is aramid fiber satin fabric, and the resin base layer 133 is carbon fiber resin matrix. The satin fabric layer 132 has high impact resistance and abrasion resistance, and has more elasticity for fracture separation than other reinforcements, including carbon fiber, ensuring the compatibility of the honeycomb structure 130 with the surface structure of the casing 110. At the same time, the aramid fiber satin fabric and the carbon fiber resin matrix are used together to obtain a strong and tough composite material, thereby protecting the honeycomb layer 131.

[0050] Furthermore, a heat insulation layer 134 is provided on the side of the honeycomb structure 130 facing the outer wall 112. The heat insulation layer 134 can prevent the high-temperature air in the accommodating cavity 113 from being conducted to the honeycomb structure 130, thereby protecting the service life of the honeycomb structure 130.

[0051] This application also discloses an engine, including: a casing assembly 10, a rotor blade ring, and a fan disk 30, wherein the casing assembly 10 is a booster stage casing assembly mounted on the rear side of the fan disk 30. The rotor blade ring is disposed between adjacent stationary blade rings, and the rotor blade ring includes a plurality of rotor blades 200 arranged circumferentially thereafter. At least a portion of the honeycomb structure 130 corresponds to the rotor blades 200 along the radial direction Y. Therefore, in the event of a rotor blade 200 detachment anomaly, the energy of the detached rotor blade 200 is absorbed, preventing the rotor blade 200 from flying out of the casing 110 and ensuring the engine's safety performance.

[0052] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any variations and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the invention, fall within the protection scope defined by the claims of the present invention.

Claims

1. A housing assembly (10) with containment capacity, characterized in that, include: Casing (110); Stator blades (120) are disposed in the inner cavity of the casing (110). The stator blades (120) are provided with a plurality of stator blade rings along the circumference of the casing assembly (10). The stator blade rings are provided with a plurality of stator blade rings along the axial direction (X) of the casing assembly (10). Rotor blade rings are provided between adjacent stator blade rings. The rotor blade rings include a plurality of rotor blades (200) arranged along their own circumference. A honeycomb structure (130) is provided on the periphery of the casing (110), at least a portion of the honeycomb structure (130) corresponding to the rotor blade (200) in the radial (Y) direction of the casing assembly (10).

2. The casing assembly (10) according to claim 1, characterized in that, The honeycomb structure (130) is offset from the stator blade (120) along the radial direction (Y).

3. The casing assembly (10) according to claim 2, characterized in that, A portion of the honeycomb structure (130) corresponds along the radial direction (Y) to the gap between the stator blade (120) and the rotor blade (200), and another portion corresponds along the radial direction (Y) to the rotor blade (200).

4. The casing assembly (10) according to claim 1, characterized in that, The honeycomb structure (130) is positioned to correspond to the first-stage rotor blade (200), and the first-stage rotor blade (200) is the rotor blade (200) of multiple rotor blade rings that is closer to the fan disk mounting side.

5. The casing assembly (10) according to claim 3, characterized in that, The casing (110) includes an inner wall (111) and an outer wall (112). The inner wall (111) surrounds the inner cavity in which the stator blade (120) is disposed, and the outer wall (112) surrounds the inner wall (111) and together with the inner wall (111) forms a receiving cavity (113). The honeycomb structure (130) is disposed in the accommodating cavity (113).

6. The casing assembly (10) according to claim 5, characterized in that, The inner wall (111) has a first positioning rib (114) on its surface facing the receiving cavity (113), and the first positioning rib (114) is arranged in pairs along the axial direction (X). In the paired first positioning ribs (114), one of them is positioned along the radial direction (Y) corresponding to the gap between the stator blade (120) and the rotor blade (200), and the other is positioned along the radial direction (Y) corresponding to the rotor blade (200). The paired first positioning ribs (114) form an installation groove to accommodate the honeycomb structure (130).

7. The casing assembly (10) according to claim 6, characterized in that, Multiple honeycomb structures (130) are provided along the axial direction (X), and multiple pairs of the first positioning ribs (114) are provided along the axial direction (X).

8. The casing assembly (10) according to claim 5, characterized in that, The honeycomb structure (130) is fitted to the inner wall (111) and spaced apart from the outer wall (112).

9. The casing assembly (10) according to claim 1, characterized in that, The stator blade (120) is an aluminum-based composite material.

10. The casing assembly (10) according to claim 1, characterized in that, The honeycomb structure (130) includes a honeycomb layer (131), a satin fabric layer (132), and a resin base layer (133); Multiple layers of satin fabric (132) are laid on both opposite end faces of the honeycomb layer (131), and a resin base layer (133) is provided between adjacent satin fabric layers (132).

11. An engine, characterized in that, include: The casing assembly (10) according to any one of claims 1 to 9; A rotor blade ring is disposed between adjacent stationary blade rings, the rotor blade ring including a plurality of rotor blades (200) arranged circumferentially along the casing assembly (10), at least a portion of the honeycomb structure (130) corresponding to the rotor blades (200) along the radial direction (Y).

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