An intermediate pressure compressor rotor-stator casing assembly structure in an aero-engine and a method thereof

Abstract

The application specifically relates to an assembly structure of a mid-pressure compressor rotor-stator casing of an aero-engine and a method thereof, wherein the assembly structure of the mid-pressure compressor rotor-stator casing of the aero-engine comprises: two-stage rotor outer casings which are integral ring structures, the rear end of the front-stage rotor outer casing is provided with a rear end stop groove, and the front end of the rear-stage rotor outer casing is provided with a front end stop groove; a plurality of stator sector blocks which comprise arc-shaped upper edge plates, arc-shaped lower edge plates and a plurality of stator blades; each stator sector block is arranged between the two rotor outer casings and is spliced to form an integral ring structure, wherein the two ends of each arc-shaped upper edge plate are positioned between the two-stage rotor outer casings through a stop opening, and an intermediate stop groove is arranged on one arc-shaped upper edge plate; a stop strip is arranged in the rear end stop groove, the front end stop groove and the intermediate stop groove; and a stator outer casing which is a horizontally split casing is arranged between the two-stage rotor outer casings and is used for pressing the arc-shaped upper edge plates and the stop strips thereon against the two-stage rotor outer casings.

Description

An assembly structure and method for the compressor stator casing in an aero-engine Technical Field

[0001] This application belongs to the technical field of compressor-stator casing assembly design in aero-engines, specifically relating to an assembly structure and method for a compressor-stator casing in aero-engines. Background Technology

[0002] In aero-engine compressors, there are multiple stages of rotors and stators. To improve assembly characteristics, the outer casing is usually designed as a split casing. During assembly, the rotor section is assembled first, and then the outer casing is assembled from the outside. The two halves of the split outer casing are connected by bolts using mounting edges. This technical solution has the following drawbacks:

[0003] 1) The outer casing adopts a split design, resulting in uneven circumferential stiffness and uncoordinated thermal deformation, which can easily aggravate the rubbing between the rotor and stator, leading to an increase in the blade tip clearance of the rotor blades and damage to the compressor performance.

[0004] 2) The split-type outer casing is connected by bolts using the mounting edge, which has poor sealing performance and is prone to gas leakage, further damaging the compressor performance.

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

[0006] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this invention, 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

[0007] The purpose of this application is to provide an assembly structure and method for the compressor-stator casing in an aero-engine, so as to overcome or mitigate at least one of the known technical defects.

[0008] The technical solution of this application is:

[0009] One aspect provides an assembly structure for the compressor stator casing in an aero-engine, including:

[0010] The two-stage rotor outer casing is a ring structure, which is arranged opposite to each other and is fitted around the outer periphery of the adjacent two-stage rotor blades. The rear end of the front stage rotor outer casing has a rear end stop groove, and the front end of the rear stage rotor outer casing has a front end stop groove.

[0011] Multiple stator sector blocks, including an arc-shaped upper edge plate, an arc-shaped lower edge plate set inside the arc-shaped upper edge plate, and multiple stator blades formed between the arc-shaped upper edge plate and the arc-shaped lower edge plate; each stator sector block is set between two rotor outer casings and spliced ​​together to form a complete ring structure, wherein each arc-shaped upper edge plate has a stop groove between its two ends and the two-stage rotor outer casings for positioning, and one arc-shaped upper edge plate has a middle stop groove;

[0012] Stop bars are installed in the rear stop groove, the front stop groove, and the middle stop groove;

[0013] The stator outer casing is a horizontally split casing, located between the two-stage rotor outer casings. Both ends are connected to the two-stage rotor outer casings by bolts through the mounting edges, pressing each arc-shaped upper edge plate and its stop strip onto the two-stage rotor outer casing.

[0014] The two stator outer casing halves are connected by bolts through the mounting edge.

[0015] According to at least one embodiment of this application, the above-described compressor-stator casing assembly structure for an aero-engine further includes:

[0016] Two M-shaped sealing rings with notches are fitted around the outer periphery of the two-stage rotor outer casing, located between the two ends of each arc-shaped upper edge plate and the end face of the two-stage rotor outer casing.

[0017] According to at least one embodiment of this application, in the above-described compressor-stator casing assembly structure for an aero-engine, the following features are characterized:

[0018] The mounting edge on one half of the stator outer casing has a folded edge that presses against the mounting edge on the other half of the stator outer casing;

[0019] The compressor stator casing assembly structure in the aero-engine also includes:

[0020] Two U-shaped sealing strips cover the mounting edges of the two stator outer casings.

[0021] On the other hand, a method for assembling the compressor stator casing in an aero-engine is provided, including:

[0022] The rotor outer casing of the preceding stage is installed onto the outer periphery of the rotor blades of the corresponding stage.

[0023] Each stator sector block is spliced ​​together, and the front end of each arc-shaped upper edge plate is positioned with the rear end of the front stage rotor outer casing.

[0024] The rear stage rotor outer casing is then installed onto the outer periphery of the corresponding stage rotor blades, with its front end positioned between the stop and the rear end of each arc-shaped upper edge plate.

[0025] Insert the stop strip into the rear stop groove, the middle stop groove, and the front stop groove;

[0026] Break open the two M-type sealing rings and put them on the outer periphery of the two-stage rotor outer casing, between the two ends of each arc-shaped upper edge plate and the end face of the two-stage rotor outer casing.

[0027] The two halves of the stator outer casing are installed between the two-stage rotor outer casing, and the two ends are connected to the two-stage rotor outer casing by bolts through the mounting edges;

[0028] Two U-shaped sealing strips are wrapped around the mounting edges of the two stator outer casings and connected with bolts to press each arc-shaped upper edge plate, its stop strip, and the two M-shaped sealing rings onto the two-stage rotor outer casing. Attached Figure Description

[0029] Figure 1 is a schematic diagram of the compressor stator casing assembly structure in an aero-engine provided in an embodiment of this application;

[0030] Figure 2 is a schematic diagram of the connection between the two halves of the stator outer casing via bolts through the mounting edge provided in the embodiment of this application;

[0031] Figure 3 is a sectional view along line AA of Figure 2;

[0032] Figure 4 is a schematic diagram of the rotor outer casing provided in an embodiment of this application;

[0033] Figure 5 is a sectional view along the BB direction of Figure 4;

[0034] Figure 6 is a partial view of Figure 5 from direction C;

[0035] Figure 7 is a schematic diagram of the two-half stator outer casing provided in an embodiment of this application;

[0036] Figure 8 is a sectional view along the DD direction of Figure 7;

[0037] Figure 9 is a schematic diagram of the stator sector block provided in an embodiment of this application;

[0038] Figure 10 is a view from direction E in Figure 9;

[0039] Figure 11 is a schematic diagram of the M-type sealing ring provided in an embodiment of this application;

[0040] Figure 12 is a schematic diagram of the cross-section of the M-type sealing ring provided in an embodiment of this application;

[0041] Figure 13 is a schematic diagram of the cross-section of the U-shaped sealing strip provided in an embodiment of this application;

[0042] in:

[0043] 1-Rotor outer casing; 2-Rotor blade; 3-Stator sector block; 4-Arc-shaped upper edge plate; 5-Arc-shaped lower edge plate; 6-Stator blade; 7-Stop strip; 8-M-type sealing ring; 9-U-type sealing strip; 10-Stator outer casing.

[0044] 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

[0045] 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.

[0046] 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.

[0047] 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.

[0048] The present application will now be described in further detail with reference to Figures 1 to 13.

[0049] One aspect provides an assembly structure for the compressor stator casing in an aero-engine, including:

[0050] The two-stage rotor outer casing 1 is a ring structure, which is arranged opposite to each other and is fitted around the outer periphery of the adjacent two-stage rotor blades 2. The rear end of the front stage rotor outer casing 1 has a rear end stop groove, and the front end of the rear stage rotor outer casing 1 has a front end stop groove.

[0051] Multiple stator sector blocks 3 include an arc-shaped upper edge plate 4, an arc-shaped lower edge plate 5 disposed within the arc-shaped upper edge plate 4, and multiple stator blades 6 formed between the arc-shaped upper edge plate 4 and the arc-shaped lower edge plate 5; each stator sector block 3 is disposed between two rotor outer casings 1 and spliced ​​together to form a complete ring structure, wherein each arc-shaped upper edge plate 4 is positioned at both ends with a stop between the two-stage rotor outer casings 1, and an arc-shaped upper edge plate 4 has a middle stop groove;

[0052] Stop strip 7 is provided in the rear stop groove, the front stop groove, and the middle stop groove;

[0053] The stator outer casing 10 is a horizontally split casing, which is set between the two-stage rotor outer casing 1. Both ends are connected to the two-stage rotor outer casing 1 by bolts through the mounting edges, pressing each arc-shaped upper edge plate 4 and its stop strip 7 onto the two-stage rotor outer casing 1.

[0054] The two halves of the stator outer casing 10 are connected by bolts through the mounting edge.

[0055] Regarding the compressor rotor-stator casing assembly structure of the aero-engine disclosed in the above embodiments, those skilled in the art will understand that its design of the compressor outer casing adopts a structure with alternating layouts of a full-ring casing and split casings. The rotor outer casing 1 with a full-ring form around the rotor blades 2 has uniform circumferential stiffness and coordinated thermal deformation, which can reduce friction between the rotor and stator and avoid increasing the blade tip clearance of the rotor blades 2, thus preventing damage to the compressor performance. The stator outer casing 10 with a split form around the stator sector block 3 can ensure the assemblability of the compressor and facilitate assembly. The specific assembly process can refer to the compressor rotor-stator casing assembly method of the aero-engine disclosed in the embodiments of this application.

[0056] Regarding the compressor stator casing assembly structure of the aero-engine disclosed in the above embodiments, those skilled in the art will understand that its design consists of stator sector blocks 3 composed of an arc-shaped upper edge plate 4, an arc-shaped lower edge plate 5, and stator blades 6, which are spliced ​​together between the two-stage rotor outer casing 1 to form a complete ring structure. Axial positioning is achieved by using the stop between the two-stage rotor outer casing 1 and decoupling from the stator outer casing 10 in the axial direction, which greatly facilitates assembly. Furthermore, the stop strip 7 is used to restrict the circumferential rotation of each stator sector block 3 relative to the two-stage rotor outer casing 1, and the two halves of the stator outer casing 10 are used to constrain the radial position of each stator sector block 3. The overall structure is simple, compact, and stable.

[0057] In the compressor-stator casing assembly structure of the aero-engine disclosed in the above embodiments, the bolt holes on the mounting edge connecting the two-stage rotor outer casing 1 and the stator outer casing 10 are equipped with offset holes for circumferential positioning to avoid circumferential misalignment during assembly.

[0058] In the compressor stator casing assembly structure of the aero-engine disclosed in the above embodiments, the radial dimensions between the rear end stop groove and the front end stop groove of the two-stage rotor outer casing 1 are different, which can avoid the incorrect assembly of each stator sector block 3.

[0059] In some optional embodiments, the above-described compressor-stator casing assembly structure for an aero-engine further includes:

[0060] Two M-shaped sealing rings 8, with notches, are fitted around the outer periphery of the two-stage rotor outer casing 1, located between the two ends of each arc-shaped upper edge plate 4 and the end face of the two-stage rotor outer casing 1, in order to reduce the possibility of gas leakage from each stator sector block 3 to the outside of the two-stage rotor outer casing 1, and protect the compressor performance.

[0061] In some optional embodiments, the compressor-stator casing assembly structure of the above-described aero-engine is characterized in that,

[0062] The mounting edge on one half of the stator outer casing 10 has a folded edge that presses against the mounting edge on the other half of the stator outer casing 10;

[0063] The compressor stator casing assembly structure in the aero-engine also includes:

[0064] Two U-shaped sealing strips 9 are wrapped around the mounting edges of the two stator outer casings 10 to reduce the possibility of gas leakage from between the two stator outer casings 10 and protect the compressor performance.

[0065] On the other hand, a method for assembling the compressor stator casing in an aero-engine is provided, including:

[0066] The rotor outer casing 1 of the preceding stage is installed onto the outer periphery of the rotor blade 2 of the corresponding stage;

[0067] Each stator sector block 3 is spliced ​​together, and the front end of each arc-shaped upper edge plate 4 is positioned with the rear end of the front stage rotor outer casing 1 through a stop.

[0068] The rear stage rotor outer casing 1 is installed onto the outer periphery of the corresponding stage rotor blade 2, and its front end is positioned with the stop between the rear end of each arc-shaped upper edge plate 4.

[0069] Insert the stop strip 7 into the rear stop groove, the middle stop groove, and the front stop groove;

[0070] Break open the two M-type sealing rings 8 and put them on the outer periphery of the two-stage rotor outer casing 1, and set them between the two ends of each arc-shaped upper edge plate 4 and the end face of the two-stage rotor outer casing 1.

[0071] The two halves of the stator outer casing 10 are installed between the two-stage rotor outer casing 1, and the two ends are connected to the two-stage rotor outer casing 1 by bolts through the mounting edges;

[0072] Two U-shaped sealing strips 9 are wrapped around the mounting edges of the two stator outer casings 10 and connected with bolts to press each arc-shaped upper edge plate 4, its stop strip 7, and the two M-shaped sealing rings 8 onto the two-stage rotor outer casing 1.

[0073] In the case of a multi-stage rotor and stator in the compressor of an aero-engine, a corresponding multi-stage rotor outer casing 1, stator sector block 3, and stator outer casing 10 can be designed. The rotor outer casing 1 of the intermediate stage is provided with a rear stop groove and a front stop groove at both ends to cooperate with the assembly of the stop strip 7. The specific assembly process can be repeated according to the above steps.

[0074] The compressor-stator casing assembly method for aero-engines disclosed in the above embodiments is used to assemble the compressor-stator casing assembly structure for aero-engines disclosed in the above embodiments. The description is relatively simple. For specific details, please refer to the relevant description of the compressor-stator casing assembly structure for aero-engines. The technical effects can also be referred to the technical effects of the relevant parts of the compressor-stator casing assembly structure for aero-engines. It will not be repeated here.

[0075] 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.

[0076] 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. A compressor stator casing assembly structure for an aero-engine, characterized in that, include: The two-stage rotor outer casing (1) is a ring structure, arranged opposite each other, and fitted around the outer periphery of the adjacent two-stage rotor blades (2). The rear end of the front-stage rotor outer casing (1) has a rear end stop groove, and the front end of the rear-stage rotor outer casing (1) has a front end stop groove. Multiple stator sector blocks (3) include an arc-shaped upper edge plate (4), an arc-shaped lower edge plate (5) arranged within the arc of the arc-shaped upper edge plate (4), and multiple stator blades (6) formed between the arc-shaped upper edge plate (4) and the arc-shaped lower edge plate (5). Each stator sector block (3) is arranged between the two rotor outer casings (1) and spliced ​​together to form a ring structure. The upper edge plate (4) of each arc is positioned between the two ends of the upper edge plate (4) and the outer casing (1) of the two-stage rotor. The outer surface of the upper edge plate (4) has a middle stop groove. The stop strip (7) is set in the rear stop groove, the front stop groove and the middle stop groove. The stator outer casing (10) is a horizontal split casing, which is set between the outer casing (1) of the two-stage rotor. The two ends are connected to the outer casing (1) of the two-stage rotor by bolts through the mounting edge, and the upper edge plate (4) and its stop strip (7) are pressed on the outer casing (1) of the two-stage rotor. The two halves of the stator outer casing (10) are connected by bolts through the mounting edge.

2. The compressor-stator casing assembly structure for an aero-engine according to claim 1, characterized in that, Also includes: Two M-shaped sealing rings (8), with notches, are fitted around the outer periphery of the two-stage rotor outer casing (1) and located between the two ends of each arc-shaped upper edge plate (4) and the end face of the two-stage rotor outer casing (1).

3. The compressor stator casing assembly structure in an aero-engine according to claim 2, characterized in that, The mounting edge on one half of the stator outer casing (10) has a folded edge that presses against the mounting edge on the other half of the stator outer casing (10); the compressor-stator casing assembly structure in the aero-engine also includes: two U-shaped sealing strips (9) that cover the mounting edges on the two half stator outer casings (10).

4. A method for assembling a compressor-stator casing in an aero-engine, used to assemble the compressor-stator casing assembly structure of the aero-engine as described in claim 3, characterized in that... include: The rotor outer casing (1) of the preceding stage is dismounted onto the outer periphery of the rotor blades (2) of the corresponding stage; Each stator sector block (3) is spliced ​​together, and the front end of each arc-shaped upper edge plate (4) is positioned with the rear end of the front stage rotor outer casing (1) at the stop; the rear stage rotor outer casing (1) is installed onto the outer periphery of the corresponding stage rotor blade (2), and its front end is positioned with the rear end of each arc-shaped upper edge plate (4) at the stop; the stop strip (7) is inserted into the rear stop groove, the middle stop groove, and the front stop groove; the two M-type sealing rings (8) are pried open and fitted onto the outer periphery of the two-stage rotor outer casings (1), and set in each Between the two ends of the arc-shaped upper edge plate (4) and the end face of the two-stage rotor outer casing (1); install the two halves of the stator outer casing (10) between the two-stage rotor outer casing (1), and connect the two ends of the stator outer casing (1) with bolts through the mounting edge; wrap the two U-shaped sealing strips (9) around the mounting edge of the two halves of the stator outer casing (10) and connect them with bolts, and press each arc-shaped upper edge plate (4) and its stop strip (7) and two M-shaped sealing rings (8) onto the two-stage rotor outer casing (1).

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