An assembly structure of a non-adjustable stator blade of a medium-pressure compressor in an aero-engine

Abstract

The application belongs to the technical field of the design of non-adjustable stator blades of a middle pressure compressor of an aero-engine, and particularly relates to an assembly structure of non-adjustable stator blades of a middle pressure compressor of an aero-engine, wherein a sealing and damping sheet is arranged in a lower edge plate mounting groove on the outer side of each arc segment of an inner ring of a stator, the gap between each non-adjustable stator blade segment and the arc segment is plugged by using a first-end and last-end insertion mode, so that the inward leakage of airflow can be reduced, the aerodynamic loss is reduced, and the relative bending between the two side edges of each sealing and damping sheet is V-shaped, the two side edges are in a pre-tightening form and are attached to the inner side of the lower edge plate of the non-adjustable stator blade segment and the outer side of the arc segment, so that the damping and vibration isolation capacity is good, the violent vibration can be avoided, and the safe operation of the compressor is ensured.

Description

Technical Field

[0001] This application belongs to the technical field of non-adjustable stator blade design for compressors in aero-engines, specifically relating to an assembly structure for non-adjustable stator blades in compressors of aero-engines. Background Technology

[0002] In aero-engines, compressor stator blades are classified into adjustable stator blades and non-adjustable stator blades according to their functions. Non-adjustable stator blades have an upper edge plate at the blade tip and a lower edge plate at the blade root. During assembly, the upper edge plate is snapped into the upper edge plate mounting slot inside the casing, and the lower edge plate is snapped into the lower edge plate mounting slot outside the stator inner ring. The inner side of the stator inner ring is sealed to the rotor components by a honeycomb structure.

[0003] Currently, for ease of assembly, compressor casings are generally designed as horizontally split structures, with the upper and lower edge plates of multiple non-adjustable stator blades connected together to form a sector-shaped segment structure. Corresponding to each sector-shaped segment of the non-adjustable stator blade, the inner ring of the stator is divided into multiple arc-shaped segments. During assembly, the lower edge plates of each sector-shaped segment of the non-adjustable stator blade can be first inserted into the mounting slots of the lower edge plates on the outer side of the arc-shaped segments of the inner ring of the stator. Then, each sector-shaped segment of the non-adjustable stator blade is divided into two groups, and the upper edge plates of the two groups of sector-shaped segments of the non-adjustable stator blade are inserted into the mounting slots of the upper edge plates on the inner side of the two halves of the horizontally split casing. Finally, the two halves of the horizontally split casing are joined together, so that the upper and lower edge plates of each sector-shaped segment of the non-adjustable stator blade and the arc-shaped segments of the inner ring of the stator form a complete ring structure.

[0004] Considering the thermal expansion problem in the compressor, after the various non-adjustable stator blade sector sections are assembled, gaps are usually designed in the circumferential direction between the upper and lower edge plates of each non-adjustable stator blade sector section and the inner ring arc section of the stator. In particular, the gaps in the circumferential direction between the lower edge plates of each non-adjustable stator blade sector section and the inner ring arc section of the stator will cause airflow to leak inward, resulting in significant aerodynamic losses. Furthermore, it weakens the ability to suppress vibration between the comb teeth, leading to severe vibration and affecting the safe operation of the compressor.

[0005] This application is made in view of the aforementioned technical deficiencies. Summary of the Invention

[0006] The purpose of this application is to provide an assembly structure for the non-adjustable stator blades of the compressor in an aero-engine, so as to overcome or mitigate at least one of the known technical defects.

[0007] The technical solution of this application is:

[0008] An assembly structure for non-adjustable stator blades of a compressor in an aero-engine, comprising:

[0009] The casing has an upper edge plate mounting groove on the inside;

[0010] The inner ring of the stator has a lower edge plate mounting groove on the outer side, which is divided into multiple arc-shaped segments with gaps between each arc-shaped segment;

[0011] Multiple non-adjustable stator blade sector segments, the lower edge plate of each non-adjustable stator blade sector segment is engaged in the lower edge plate mounting groove on the outer side of each arc segment, and there is a gap between the lower edge plates of each non-adjustable stator blade sector segment; each non-adjustable stator blade sector segment is divided into two groups, the upper edge plates of the two groups of non-adjustable stator blade sector segments are engaged in the upper edge plate mounting groove on the inner side of the two halves of the casing, and there is a gap between the upper edge plates of each non-adjustable stator blade sector segment.

[0012] Multiple sealing damping plates are installed in the mounting grooves of the lower edge plate on the outer side of each arc segment. The two sides are bent into a V shape, with one edge abutting the inner side of the lower edge plate of the non-adjustable stator blade fan segment and the other edge abutting the outer side of the arc segment.

[0013] Each sealing damping plate has one end retracted into the mounting groove of the lower edge plate on the outer side of the corresponding arc segment, and the other end protruding out of the mounting groove of the lower edge plate on the outer side of the corresponding arc segment. This end also extends into the mounting groove of the lower edge plate on the outer side of the adjacent arc segment. However, at the interface between the two halves of the casing, the length of the sealing damping plate protruding out of the mounting groove of the lower edge plate on the outer side of the corresponding arc segment does not exceed the gap between the fan-shaped segment and the arc segment of the non-adjustable stator blade.

[0014] According to at least one embodiment of this application, the above-described assembly structure of the non-adjustable stator blades of the compressor in an aero-engine further includes:

[0015] Multiple positioning pins position each sealing damping plate inside the lower edge plate of the non-adjustable stator blade fan-shaped section.

[0016] According to at least one embodiment of this application, in the above-described assembly structure of the non-adjustable stator blade of the compressor in the aero-engine, each sealing damping plate is attached to one side edge of the inner side of the lower edge plate of the corresponding non-adjustable stator blade sector segment, bent inward, and attached to the side wall of the mounting groove of the lower edge plate of the corresponding arc segment outer side.

[0017] According to at least one embodiment of this application, in the above-described assembly structure of the non-adjustable stator blade of the compressor in the aero-engine, the sealing damping plate at the interface between the two halves of the casing does not protrude from the mounting groove of the lower edge plate on the outer side of the corresponding arc segment.

[0018] According to at least one embodiment of this application, in the above-mentioned assembly structure of the non-adjustable stator blade of the compressor in the aero-engine, the angle of the sector segment and the arc segment of each non-adjustable stator blade is α.

[0019] The angle of each sealing damping plate is β, β=α, and it deviates from the corresponding non-adjustable stator blade sector segment and its arc segment by an angle δ;

[0020] The angle of the sealing damping plate at the interface between the two halves of the casing is β', β' = α - δ, and it deviates from the corresponding non-adjustable stator blade sector and arc segment by an angle of 0.5δ.

[0021] This application has at least the following beneficial technical effects:

[0022] This invention provides an assembly structure for non-adjustable stator blades in an aero-engine compressor. As will be understood by those skilled in the art, the design incorporates sealing and vibration damping plates installed in the mounting grooves on the lower edge plates of each arc segment of the inner ring of the stator. By using a head-to-tail insertion method, the gaps between the fan-shaped segments and arc segments of each non-adjustable stator blade are sealed, thereby reducing inward airflow leakage and aerodynamic losses. Furthermore, the design of each sealing and vibration damping plate features a V-shaped bend between its two sides, with the two sides pre-tightly abutting against the inner side of the lower edge plate of the fan-shaped segment and the outer side of the arc segment of the non-adjustable stator blade. This provides excellent vibration damping and isolation capabilities, thereby preventing severe vibrations and ensuring the safe operation of the compressor. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the assembly structure of the non-adjustable stator blades of the compressor in an aero-engine provided in the embodiments of this application;

[0024] Figure 2 This is a schematic diagram of the configuration of the sealing and vibration damping sheet provided in the embodiments of this application;

[0025] Figure 3 This is a schematic diagram of the sealing damping sheet not located at the interface between the two halves of the casing, and the non-adjustable stator blade fan-shaped section and the stator inner ring arc-shaped section, provided in the embodiments of this application.

[0026] Figure 4 This is a schematic diagram of the sealing damping sheet at the interface between the two halves of the casing, which is provided in the embodiments of this application, in conjunction with the fan-shaped section of the non-adjustable stator blade and the arc-shaped section of the stator inner ring.

[0027] Figure 5 This is a schematic diagram of the circumferential assembly of the various non-adjustable stator blade sector segments provided in the embodiments of this application;

[0028] in:

[0029] 1-Casing; 2-Stator inner ring; 3-Non-adjustable stator blade sector; 4-Sealing damping plate; 5-Positioning pin.

[0030] 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

[0031] 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, and other related parts can be referred to the general design.

[0032] 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 indicating direction used in this application description are used only to indicate relative direction or positional relationship; when the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "comprising" as used in this application description indicates that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, but does not exclude other elements or objects.

[0033] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable 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. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0034] An assembly structure for non-adjustable stator blades in an aero-engine compressor, such as Figure 1 As shown, it includes:

[0035] The casing 1 has an upper edge plate mounting groove on the inner side, which is a horizontal split structure, or it can be a ring structure;

[0036] The inner ring 2 of the stator has a lower edge plate mounting groove on the outer side, which is divided into multiple arc-shaped segments with gaps between each arc-shaped segment;

[0037] Multiple non-adjustable stator blade sector segments 3, the lower edge plate of each non-adjustable stator blade sector segment 3 is inserted into the lower edge plate mounting groove on the outer side of each arc segment, and there is a gap between the lower edge plates of each non-adjustable stator blade sector segment 3; each non-adjustable stator blade sector segment 3 is divided into two groups, the upper edge plates of the two groups of non-adjustable stator blade sector segments 3 are inserted into the upper edge plate mounting groove on the inner side of the two halves of the casing 1, and there is a gap between the upper edge plates of each non-adjustable stator blade sector segment 3.

[0038] Multiple sealing damping plates 4 are installed in the mounting groove of the lower edge plate on the outer side of each arc segment. The two sides are bent into a V shape, with one edge abutting the inner side of the lower edge plate of the non-adjustable stator blade fan-shaped segment 3 and the other edge abutting the outer side of the arc segment.

[0039] Each sealing damping plate 4 has one end retracted into the mounting groove of the lower edge plate on the outer side of the corresponding arc segment, and the other end protruding from the mounting groove of the lower edge plate on the outer side of the corresponding arc segment. This end extends into the mounting groove of the lower edge plate on the outer side of the adjacent arc segment. However, at the interface between the two halves of the casing 1, the length of the sealing damping plate 4 protruding from the mounting groove of the lower edge plate on the outer side of the corresponding arc segment does not exceed the gap between the non-adjustable stator blade fan-shaped segment 3 and its arc segment, so as to facilitate assembly.

[0040] Regarding the non-adjustable stator blade assembly structure of the aero-engine compressor disclosed in the above embodiments, those skilled in the art will understand that its design includes sealing damping plates 4 installed in the mounting grooves of the lower edge plates on the outer side of each arc segment of the inner ring 2 of the stator. By using a head-to-tail insertion method, the gaps between the fan-shaped segments 3 and their arc segments of each non-adjustable stator blade are sealed, thereby reducing inward leakage of airflow and reducing aerodynamic losses. Furthermore, the design of each sealing damping plate 4 with its two sides bent into a V-shape, and its two sides being pre-tightened and abutting against the inner side of the lower edge plate of the fan-shaped segment 3 of the non-adjustable stator blade and the outer side of the arc segment, provides excellent vibration reduction and isolation capabilities, thereby preventing severe vibrations and ensuring the safe operation of the compressor.

[0041] In some optional embodiments, the above-described non-adjustable stator blade assembly structure for the compressor in an aero-engine further includes:

[0042] Multiple positioning pins 5 position each sealing damping plate 4 inside the lower edge plate of the non-adjustable stator blade fan-shaped section 3, preventing the sealing damping plate 4 from circumferentially moving in the mounting groove of the lower edge plate, which would result in a poor sealing and damping effect.

[0043] In some optional embodiments, in the above-described assembly structure of the non-adjustable stator blade of the compressor in the aero-engine, each sealing damping plate 4 is attached to one side edge of the inner side of the lower edge plate of the corresponding non-adjustable stator blade sector segment 3, bent inward, and attached to the side wall of the mounting groove of the corresponding arc segment outer lower edge plate. It is supported at three points between the lower edge plate of the non-adjustable stator blade sector segment 3 and the arc segment of the stator inner ring 2, thus achieving a good vibration reduction and isolation effect. The configuration of the sealing damping plate 4 is as follows: Figure 2 As shown.

[0044] Regarding the non-adjustable stator blade assembly structure of the compressor in the aero-engine disclosed in the above embodiments, it is understood that it utilizes the protruding end of a sealing damping plate 4 set in the mounting groove of the lower edge plate on the outer side of the arc segment of each stator inner ring 2, which is inserted into the mounting groove of the adjacent lower edge plate to seal the gap between the sector segment 3 and the arc segment of each non-adjustable stator blade, reducing inward leakage of airflow and reducing aerodynamic losses. For this purpose, it is necessary to design that the angle of the protruding end of each sealing damping plate 4 is greater than the angle of the gap between the sector segment 3 and the arc segment of the non-adjustable stator blade, and the angle at which it retracts into the mounting groove of the lower edge plate on the outer side of the corresponding arc segment must provide sufficient margin for the insertion of the protruding end. The sealing damping plate 4 located at the interface between the two halves of the casing 1 should not interfere with the assembly. Based on this, for ease of processing and inspection, in a specific embodiment, the angle of the sector segment 3 and the arc segment of each non-adjustable stator blade is designed as α; the angle of each sealing damping plate 4 is β, β = α, and the deviation angle from the corresponding sector segment 3 and the arc segment of the non-adjustable stator blade is δ, such as... Figure 3 As shown, one end of the sealing damping plate 4 is recessed into the mounting groove of the lower outer edge plate of the corresponding arc segment by an angle δ, and the other end protrudes out of the mounting groove of the lower outer edge plate of the corresponding arc segment by an angle δ. δ is greater than the angle of the gap between the non-adjustable stator blade fan-shaped segment 3 and its arc segment.

[0045] The angle of the sealing damping plate 4 at the interface between the two halves of the casing 1 is β', β' = α - δ, and it deviates from the corresponding non-adjustable stator blade sector segment 3 and its arc segment by an angle of 0.5δ, such as Figure 4 As shown, the sealing damping plate 4, which is designed to be located at the interface between the two halves of the casing 1, has one end protruding from the mounting groove angle δ of the lower edge plate on the outer side of the corresponding arc segment and is inserted into the mounting groove of the lower edge plate on the outer side of the adjacent arc segment. The other end is located on the interface between the two halves of the casing 1 and does not protrude from the mounting groove of the lower edge plate on the outer side of the corresponding arc segment.

[0046] The circumferential assembly of each non-adjustable stator blade sector segment 3, such as... Figure 5 As shown, the sealing damping plate 4 located at the interface between the two halves of the casing 1 can only be... Figure 5 Two medium-dark colors.

[0047] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. Similar or identical parts between embodiments can be referred to mutually. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined to obtain new embodiments.

[0048] 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 scope of protection 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 scope of protection of this application.

Claims

1. An assembly structure for non-adjustable stator blades of a compressor in an aero-engine, characterized in that, include: The casing (1) has an upper edge plate mounting groove on the inner side; The inner ring (2) of the stator has a lower edge plate mounting groove on the outer side, which is divided into multiple arc segments with gaps between each arc segment; Multiple non-adjustable stator blade sector segments (3), the lower edge plate of each non-adjustable stator blade sector segment (3) is inserted into the lower edge plate mounting groove on the outer side of each arc segment, and there is a gap between the lower edge plates of each non-adjustable stator blade sector segment (3); each non-adjustable stator blade sector segment (3) is divided into two groups, the upper edge plates of the two groups of non-adjustable stator blade sector segments (3) are inserted into the upper edge plate mounting groove on the inner side of the two halves of the casing (1), and there is a gap between the upper edge plates of each non-adjustable stator blade sector segment (3); Multiple sealing damping plates (4) are installed in the mounting groove of the lower edge plate on the outer side of each arc segment. The two sides are bent into a V shape, with one edge abutting the inner side of the lower edge plate of the non-adjustable stator blade fan segment (3) and the other edge abutting the outer side of the arc segment. Each sealing damping plate (4) has one end retracted into the mounting groove of the lower edge plate on the outer side of the corresponding arc segment, and the other end protrudes out of the mounting groove of the lower edge plate on the outer side of the corresponding arc segment. The end of this end extends into the mounting groove of the lower edge plate on the outer side of the adjacent arc segment. However, the length of the end of the sealing damping plate (4) protruding out of the mounting groove of the lower edge plate on the outer side of the corresponding arc segment at the interface between the two halves of the casing (1) does not exceed the gap between the non-adjustable stator blade fan-shaped segment (3) and its arc segment.

2. The assembly structure of the non-adjustable stator blades of the compressor in an aero-engine according to claim 1, characterized in that, Also includes: Multiple positioning pins (5) position each sealing damping plate (4) on the inner side of the lower edge plate of the non-adjustable stator blade fan-shaped section (3).

3. The assembly structure of the non-adjustable stator blades of the compressor in an aero-engine according to claim 1, characterized in that, Each sealing damping plate (4) is attached to one side edge of the inner side of the lower edge plate of the corresponding non-adjustable stator blade fan-shaped section (3), bent inward, and attached to the side wall of the mounting groove of the lower edge plate of the corresponding arc-shaped section.

4. The assembly structure of the non-adjustable stator blades of the compressor in an aero-engine according to claim 1, characterized in that, The sealing damping plate (4) at the interface between the two halves of the casing (1) does not protrude from the mounting groove of the lower edge plate on the outer side of the corresponding arc segment.

5. The assembly structure of the non-adjustable stator blades of the compressor in an aero-engine according to claim 1, characterized in that, The angle of each non-adjustable stator blade fan-shaped segment (3) and its arc-shaped segment is α; The angle of each sealing damping plate (4) is β, β=α, and it deviates from the corresponding non-adjustable stator blade fan-shaped segment (3) and its arc segment by an angle δ; The angle of the sealing damping plate (4) located at the interface between the two halves of the casing (1) is β', β' = α - δ, and it deviates from the corresponding non-adjustable stator blade fan-shaped segment (3) and its arc segment by an angle of 0.5δ.

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