compressor

Abstract

The application provides a compressor, which comprises a compressor stator, a compressor rotor and a compressor blade outer ring. The compressor stator comprises a stator casing, a blade outer ring and a blade outer ring elastic supporting element. The stator casing is cylindrical. The blade outer ring is arranged on the inner circumferential surface of the stator casing. The blade outer ring is movably connected to the stator casing along the radial direction of the compressor. The blade outer ring elastic supporting element is arranged between the blade outer ring and the stator casing. The blade outer ring elastic supporting element can be elastically compressed and deformed in the radial direction of the compressor stator, and has a tendency to hinder the movement of the blade outer ring to the radial outside. The compressor rotor is in clearance fit with the blade outer ring in the radial direction. When the compressor rotor contacts the blade outer ring, the blade outer ring elastic supporting element is elastically compressed and deformed.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aero-engines, and particularly relates to a compressor. BACKGROUND

[0002] Titanium alloy has good specific stiffness, specific strength and high heat resistance, and is a key material for reducing the structural weight and improving the thrust-to-weight ratio of high-performance engines. At present, titanium alloy has been widely used in aero-engines as the material of compressor casings, blades, disk and fan ducts and other components.

[0003] Titanium alloy needs certain temperature and pressure conditions to catch fire. The working temperature of titanium alloy components in an aero-engine is much lower than the ignition point of titanium alloy, and will not cause titanium fire under normal conditions. However, when the components made of titanium alloy and other components are subjected to severe impact and rubbing, a large amount of heat will be generated. Titanium alloy is a poor conductor of heat, and the heat cannot be effectively conducted and dissipated. This can cause the local temperature of the component to rise, and when it exceeds the ignition point of titanium alloy, titanium fire will occur under certain pressure and oxygen concentration, which will have a serious impact on the engine.

[0004] In view of the requirement of preventing titanium fire, the prior art generally uses an abrasion-resistant coating to avoid direct contact between titanium alloys, and uses a gap design to avoid rubbing between titanium alloys. Although the prior art can reduce the risk of titanium fire to some extent, if the thickness of the coating is not reasonably designed or the coating falls off, the titanium fire prevention design will fail. SUMMARY

[0005] The present application aims to provide a compressor which can reduce the risk of titanium fire.

[0006] Embodiments of the present application provide a compressor, comprising:

[0007] a compressor stator, the compressor stator comprising a stator casing, a blade outer ring and a blade outer ring elastic support element, the stator casing being cylindrical, the blade outer ring being arranged on the inner circumferential surface of the stator casing, the blade outer ring being movably connected to the stator casing in the radial direction of the compressor, the blade outer ring elastic support element being arranged between the blade outer ring and the stator casing, the blade outer ring elastic support element being elastically compressively deformed in the radial direction of the compressor stator and having a tendency to hinder the movement of the blade outer ring to the radial outside; and

[0008] a compressor rotor, the compressor rotor being in clearance fit with the blade outer ring in the radial direction, and causing the blade outer ring elastic support element to be elastically compressively deformed when the compressor rotor touches the blade outer ring.

[0009] In at least one possible implementation, the compressor rotor comprises a rotor disk and a plurality of rotor blades connected to the rotor disk in a circumferential arrangement of the compressor, the rotor blades being aligned with the outer shroud in an axial direction of the compressor.

[0010] In at least one possible implementation, the outer shroud and / or the rotor blades are made of a titanium alloy.

[0011] In at least one possible implementation, the outer shroud and the rotor blades are a clearance fit.

[0012] In at least one possible implementation, the outer shroud is provided with a plurality of outer shrouds spaced apart from each other in a circumferential direction of the compressor.

[0013] In at least one possible implementation, an inner circumferential surface of the outer shroud is coated with an abradable coating.

[0014] In at least one possible implementation, the compressor stator further comprises stator blades connected to an inner circumferential surface of the stator casing, a stator inner shroud movably connected to the stator blades in a radial direction of the compressor relative to the stator blades, and a stator inner shroud elastic support element provided between the stator blades and the stator inner shroud, the stator inner shroud elastic support element having a tendency to hinder movement of the stator inner shroud to a radially outer side.

[0015] In at least one possible implementation, the rotor disk is provided with a radially outwardly protruding labyrinth, the stator inner shroud being aligned with the labyrinth in an axial direction of the compressor.

[0016] In at least one possible implementation, the outer shroud elastic support element and / or the stator inner shroud elastic support element has a cross-sectional shape of a wave or a W.

[0017] In at least one possible implementation, the outer shroud elastic support element and / or the stator inner shroud elastic support element is made of a shape memory alloy.

[0018] By adopting the above technical solution, the rubbing pressure between the compressor stator and the compressor rotor is dynamically adjusted by the elastically floating outer shroud, the rubbing heat is reduced, and the risk of titanium fire is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0019] Fig. 1 A partial structural schematic diagram of a compressor according to an embodiment of the present application is shown.

[0020] Fig. 2A structural diagram of a blade outer ring elastic support element of a compressor according to an embodiment of the present application is shown.

[0021] Fig. 3 A structural diagram of a blade outer ring elastic support element of a compressor according to another embodiment of the present application is shown.

[0022] BRIEF DESCRIPTION OF DRAWINGS

[0023] 1 compressor stator 11 stator casing 12 blade outer ring 13 blade outer ring elastic support element 14 stator vane 15 stator inner ring 16 stator inner ring elastic support element

[0024] 2 compressor rotor 21 rotor disk 22 rotor blade 23 labyrinth

[0025] A axial R radial DETAILED DESCRIPTION

[0026] In order to more clearly illustrate the above and other features and advantages of the present application, a more particular description of the application briefly described above will be rendered by reference to specific embodiments thereof, which are illustrated in the appended drawings. The embodiments described in this section are intended to be illustrative only and are not intended to limit the scope of the application. The scope of the application shall be defined by the appended claims. For a better understanding of the present application, reference will now be made to the accompanying drawings.

[0027] As shown in the drawings, embodiments of the present application propose an aero-engine with low titanium fire risk, the aero-engine comprising a compressor. Figs. 1 to 3

[0028] The compressor comprises a compressor stator 1 and a compressor rotor 2, the compressor stator 1 is cylindrical, the compressor stator 1 surrounds the compressor rotor 2, and the compressor rotor 2 can rotate relative to the compressor stator 1.

[0029] (compressor stator)

[0030] The compressor stator 1 comprises a stator casing 11, a blade outer ring 12, a blade outer ring elastic support element 13, a stator vane 14, a stator inner ring 15, and a stator inner ring elastic support element 16.

[0031] The stator casing 11 is cylindrical, and the blade outer ring 12 is arranged on the inner circumferential surface of the stator casing 11. Specifically, the inner circumferential surface of the stator casing 11 is provided with a mounting groove, the cross section of the mounting groove can be T-shaped, the blade outer ring 12 can be provided with a mounting portion, the cross section of the mounting portion can be T-shaped, and the mounting portion can be embedded in the mounting groove. The mounting portion can move in the depth direction of the mounting groove (the radial direction R of the compressor) in the mounting groove, so that the blade outer ring 12 can move relative to the stator casing 11 along the radial direction R of the compressor.​

[0032] The outer shroud 12 can be arc-shaped, and a plurality of outer shrouds 12 can be provided in a ring shape at intervals in the circumferential direction of the compressor, so that the plurality of outer shrouds 12 can have a movement space.

[0033] The outer shroud elastic support element 13 is arranged between the outer shroud 12 and the stator casing 11, for example, the outer shroud elastic support element 13 is arranged at the bottom of the mounting groove, and the outer shroud 12 is pressed against the opening of the mounting groove by the outer shroud elastic support element 13 and cannot be taken out of the mounting groove. The outer shroud elastic support element 13 can be elastically compressed and deformed in the radial direction of the compressor stator 1, and the outer shroud elastic support element 13 has a tendency to hinder the movement of the outer shroud 12 to the radial outside. The outer shroud 12 is mounted on the stator casing 11 by the outer shroud elastic support element 13, so that the outer shroud 12 is convenient to maintain and replace, and the maintenance cost is low.

[0034] Further, the inner circumferential surface of the outer shroud 12 is coated with an abradable coating 121, which can include aluminum, copper or nickel-based composite materials, and the abradable coating 121 separates the outer shroud 12 from the compressor rotor 2. The material of the outer shroud 12 is titanium alloy.

[0035] As shown in Fig. 2 , the outer shroud elastic support element 13 can be arc-shaped and sheet-shaped, and the cross section (i.e. radial section) of the outer shroud elastic support element 13 can be wave-shaped, for example, W-shaped. As shown in Fig. 3 , in other possible embodiments, the cross section of the outer shroud elastic support element 13 can be C-shaped, and the middle part of the C-shaped can protrude towards the opening side of the C-shaped. It can be understood that the outer shroud elastic support element 13 as a whole can be arc-shaped and sheet-shaped, Fig. 2 , and Fig. 3 only its cross section is shown, which can extend arcuately in the direction perpendicular to the paper (i.e. circumferential direction).

[0036] The inner shroud 15 is connected to the stator vane 14, and the inner shroud 15 can move along the radial direction R relative to the stator vane 14. The inner shroud elastic support element 16 is arranged between the inner shroud 15 and the stator vane 14, and the inner shroud elastic support element 16 has a tendency to hinder the movement of the inner shroud 15 to the radial outside.

[0037] The connection structure of the inner shroud 15 and the stator vane 14 can be the same as or similar to the connection structure of the outer shroud 12 and the stator casing 11, and the stator vane 14 can be provided with a T-shaped groove, and the inner shroud 15 is mounted and embedded in the T-shaped groove.

[0038] The shape of the elastic support element 13 of the outer ring of the moving blade and the elastic support element 16 of the inner ring of the stationary blade can be the same or different. In the present embodiment, the shape of the elastic support element 13 of the outer ring of the moving blade and the elastic support element 16 of the inner ring of the stationary blade are different.

[0039] The elastic support element 13 of the outer ring of the moving blade and / or the elastic support element 16 of the inner ring of the stationary blade can be made of a shape memory alloy (such as a titanium-nickel-based high-temperature memory alloy), and has elasticity. The shape memory alloy has different sizes and stiffnesses at different temperatures, the size is larger and the stiffness is lower as the temperature is higher, and the gap between the rotor blade 22 and the outer ring 12 of the moving blade can be further controlled by the change of the size and the stiffness with the temperature, the risk of titanium fire is reduced, and the performance of the engine is improved.

[0040] (Compressor rotor)

[0041] The compressor rotor 2 includes a rotor disc 21 and a plurality of rotor blades 22 fixedly connected to the rotor disc 21, and the plurality of rotor blades 22 are connected to the rotor disc 21 in a circumferential arrangement of the compressor. In the axial direction A of the compressor, the rotor blades 22 are aligned with the outer ring 12 of the moving blade, and the rotor blades 22 and the stationary blades 14 are arranged in a staggered manner in the axial direction A.

[0042] The material of the rotor blade 22 can be titanium alloy. The outer ring 12 of the moving blade and the rotor blade 22 are in a clearance fit, and when the rotor blade 22 collides with the outer ring 12 of the moving blade due to, for example, manufacturing, assembly errors or environmental influences, the elastic support element 13 of the outer ring 12 of the moving blade can be extruded, and the floating outer ring 12 of the moving blade can reduce the collision pressure between the outer ring 12 of the moving blade and the rotor blade 22, reduce the collision heat, and thus reduce the risk of titanium fire.

[0043] The rotor disc 21 is provided with a gill 23 protruding outward in the radial direction, and in the axial direction A of the compressor, the inner ring 15 of the stationary blade can be aligned with the gill 23, and the floating inner ring 15 of the stationary blade can reduce the collision pressure between the gill 23 and the inner ring 15 of the stationary blade, reduce the collision heat, and fundamentally eliminate or reduce the occurrence of the titanium fire generation condition, thereby reducing the risk of titanium fire.

[0044] The operating gap between the compressor stator 1 and the compressor rotor 2 in the compressor of the present application can be dynamically adjusted by the elastic support element, so that the compressor stator 1 and the compressor rotor 2 are in a clearance fit, even if contact occurs, it is an elastic contact, which reduces the collision pressure, and further reduces the collision heat, thereby reducing the risk of titanium fire.

[0045] It should be understood that at least part of the aspects or features of the above-mentioned embodiments, examples or examples can be appropriately combined.

[0046] It can be understood that, in the present application, the number of components or members is one or more when the number of components or members is not particularly limited, and the plurality herein refers to two or more. For the case where the number of components or members is specifically described as, for example, two, three, four, etc. in the drawings and / or the description, the specific number is generally exemplary and not restrictive, and it can be understood as a plurality, i.e., two or more, but this does not mean that the present application excludes the case of one.

[0047] In the present application, unless otherwise explicitly stated or limited, the terms "mounting", "assembling", "assembly", "connecting", "connection", "coupling", "linking", "abutting", "communicating", "communicating", "conducting", "fixing", "fastening", and the like should be understood in a broad sense, for example, they can be direct or indirect. For example, in terms of connection, it can be a fixed connection, or a detachable connection, or integrated; it can be a mechanical connection, or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise explicitly stated or limited. For example, in terms of communication / conduction, etc., it can be direct communication / conduction, or indirect communication / conduction via an intermediate medium. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0048] In the present application, unless otherwise explicitly stated or limited, one member is disposed in / installed in / located in / contained in / placed in another member, etc. can be any of the following two cases: a part or most of the one member is located in the other member; and the one member is completely contained in the other member.

[0049] Although the present application has been described in detail using the above embodiments, it is clear to those skilled in the art that the present application is not limited to the embodiments described in the present specification. The present application can be modified and implemented as a modified embodiment without departing from the spirit and scope of the present application defined by the claims. Therefore, the description in the present specification is for the purpose of illustration and does not have any limiting meaning on the present application.

Claims

1. A compressor, characterized in that, include: The compressor stator (1) includes a stator housing (11), a moving blade outer ring (12), and a moving blade outer ring elastic support element (13). The stator housing (11) is cylindrical, and an mounting groove is provided on the inner circumferential surface of the stator housing (11). The cross-section of the mounting groove is T-shaped. The moving blade outer ring (12) is disposed on the inner circumferential surface of the stator housing (11). The moving blade outer ring (12) can be movably connected to the stator housing (11) along the radial direction (R) of the compressor relative to the stator housing (11). The moving blade outer ring (12) is provided with a mounting part. The cross-section of the mounting part is T-shaped, and the mounting part is embedded in the... The mounting slot, wherein the mounting part is movable in the mounting slot along the radial direction (R), the moving blade outer ring elastic support element (13) is disposed between the moving blade outer ring (12) and the stator casing (11), the moving blade outer ring elastic support element (13) is disposed between the bottom of the mounting slot and the mounting part, the moving blade outer ring (12) is pressed against the opening of the mounting slot by the moving blade outer ring elastic support element (13) and will not come out of the mounting slot, the moving blade outer ring elastic support element (13) is capable of elastic compression deformation in the radial direction of the compressor stator (1) and has a tendency to prevent the moving blade outer ring (12) from moving radially outward; as well as The compressor rotor (2) is in radial clearance fit with the outer ring (12) of the moving blade. When the compressor rotor (2) touches the outer ring (12), the elastic support element (13) of the outer ring of the moving blade undergoes elastic compression deformation. The compressor rotor (2) includes a rotor disk (21) and multiple rotor blades (22). The outer ring (12) of the moving blade and the rotor blade (22) are in clearance fit. The compressor stator (1) further includes stator blades (14), a stator blade inner ring (15), and a stator blade inner ring elastic support element (16). The stator blades (14) are connected to the inner circumferential surface of the stator casing (11). The stator blade inner ring (15) is movably connected to the stator blades (14) along the radial direction (R) of the compressor relative to the stator blades (14). The stator blade inner ring elastic support element (16) is disposed between the stator blades (14) and the stator blade inner ring (15). The stator blade inner ring elastic support element (16) has a tendency to resist the radial outward movement of the stator blade inner ring (15). The outer ring elastic support element (13) of the moving blade and the inner ring elastic support element (16) of the stationary blade are made of shape memory alloy.

2. The compressor according to claim 1, characterized in that, The plurality of rotor blades (22) are connected to the rotor disk (21) in a circumferential arrangement along the compressor, and the rotor blades (22) are aligned with the outer ring (12) of the moving blade in the axial direction (A) of the compressor.

3. The compressor according to claim 2, characterized in that, The material of the outer ring (12) of the moving blade and / or the rotor blade (22) is titanium alloy.

4. The compressor according to claim 1, characterized in that, Multiple outer rings (12) of the moving blade are provided, and the multiple outer rings (12) of the moving blade are spaced apart from each other in the circumferential direction of the compressor.

5. The compressor according to claim 1, characterized in that, The inner circumferential surface of the outer ring (12) of the moving blade is coated with a wearable coating (121).

6. The compressor according to claim 1, characterized in that, The rotor disk (21) is provided with grating teeth (23) that protrude radially outward, and the inner ring (15) of the stationary vane is aligned with the grating teeth (23) in the axial direction (A) of the compressor.

7. The compressor according to claim 1, characterized in that, The cross-sectional shape of the outer ring elastic support element (13) of the moving blade and / or the inner ring elastic support element (16) of the stationary blade is wavy or W-shaped.

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