CN111486129B - Stator rectifier ring structure, compressor and aircraft engine - Google Patents
Stator rectifier ring structure, compressor and aircraft engine Download PDFInfo
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- CN111486129B CN111486129B CN202010313582.4A CN202010313582A CN111486129B CN 111486129 B CN111486129 B CN 111486129B CN 202010313582 A CN202010313582 A CN 202010313582A CN 111486129 B CN111486129 B CN 111486129B
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- rectifier
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- rectifying
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
Abstract
The invention provides a stator rectifying ring structure, a gas compressor and an aero-engine. Wherein, stator rectification unit contains the rectifier ring, and the rectifier ring is the two segmentation structures of dividing equally in half on its circumference. The rear end of the first rectifier is connected to the rectifier ring. The outer wall of the front end of second rectifier is provided with a plurality of recesses of looks spaced along circumference, and the inner wall of the rear end of rectifier ring is provided with a plurality of bosss of looks spaced along circumference, and the rectifier ring passes through the cooperation of boss and recess to be connected in the second rectifier. The split-half casing is not required to be additionally arranged, and the split-half casing is suitable for installation and positioning of the multifunctional integrated stator guide vane ring. In addition, the invention realizes the axial positioning of the rectifier ring and the rectifier by utilizing the design of the multi-section boss and the groove, and simultaneously can realize the function of preventing the rectifier ring and the rectifier from rotating relatively in the circumferential direction. Therefore, the pneumatic valve is convenient to repeatedly assemble and disassemble, high in working reliability and small in pneumatic leakage.
Description
Technical Field
The invention relates to the technical field of aero-engines and compressor structures thereof, in particular to a stator rectifier ring structure, a compressor and an aero-engine.
Background
With the development of modern aircraft engines, integrated multi-stage integral compressor rotor blade disc structures have been widely adopted in existing design schemes. At present, for stator rectifying blades between the integral disc stages, a rectifying ring which is cut into a plurality of parts in the circumferential direction is required to be matched and a mounting mode of embedding step by step is adopted. This construction generally requires additional bolted split casings to accommodate installation requirements or other stator members to assist in the clamping in a tight fit.
However, the above prior art needs to increase the adaptive half-split casing structure, needs to provide enough radial space to meet the structural requirement of the half-split casing, and has a complex structure and more parts; multiple circumferential cutting is often needed to simplify installation, which easily causes larger pneumatic leakage; during installation, repeated polishing and trial assembly are required due to small deformation of the rectifier ring, and the assembly economy is poor. In addition, the split half rectifying ring structure adopting the small interference positioning mode needs higher part machining precision and matching precision, is difficult to install and decompose, and is likely to have axial or circumferential relative motion of the guide vane, so that instability exists in the working state.
Disclosure of Invention
It is a primary object of the present invention to overcome at least one of the above-mentioned deficiencies of the prior art and to provide a stator commutation ring structure that is easy to repeatedly assemble and disassemble, has high operational reliability and has a small amount of aerodynamic leakage.
Another main object of the present invention is to overcome at least one of the drawbacks of the prior art described above, and to provide a compressor having the above-described stator commutating ring structure.
A further main object of the present invention is to overcome at least one of the drawbacks of the prior art described above and to provide an aircraft engine with a compressor as described above.
In order to achieve the purpose, the invention adopts the following technical scheme:
according to an aspect of the present invention, a stator rectifying ring structure is provided, which includes a first rectifier, a second rectifier and a stator rectifying unit. The stator rectifying unit comprises a rectifying ring, and the rectifying ring is of a two-section structure which is divided into half parts in the circumferential direction. The rear end of the first rectifier is connected to the rectifying ring and used for compressing and centering the rectifying ring. The outer wall of the front end of second rectifier is provided with a plurality of recesses of looks spaced along circumference, the inner wall of the rear end of rectifier ring is provided with a plurality of bosss of looks spaced along circumference, the rectifier ring passes through the boss with the cooperation of recess connect in the second rectifier.
According to one embodiment of the invention, the inner wall of the rear end of the first rectifier is sleeved on the outer wall of the rectifier ring.
According to one embodiment of the invention, the outer wall of the rectifier ring has two outer ring surfaces, the two outer ring surfaces are distributed along the axial direction, and the corresponding radius of the outer ring surface which is relatively far forward is smaller than that of the other outer ring surface. The inner wall of the rear end of the first rectifier is provided with two inner ring surfaces, and when the first rectifier is connected to the rectifying ring, the two inner ring surfaces are respectively pressed against the two outer ring surfaces.
According to one embodiment of the invention, the rear end of the first rectifier extends backwards and is sleeved outside the second rectifier. And a sealing ring is arranged between the inner wall of the first rectifier and the outer wall of the second rectifier.
According to one embodiment of the invention, the outer wall of the second rectifier is provided with a sealing groove along the circumferential direction, and the sealing ring is arranged in the sealing groove.
According to one embodiment of the present invention, the length of each boss in the circumferential direction is equal, and the plurality of bosses are uniformly distributed at intervals in the circumferential direction. The lengths of the grooves in the circumferential direction are equal, and the grooves are uniformly distributed at intervals in the circumferential direction.
According to another aspect of the present invention, a stator rectifying ring structure is provided, which includes a first rectifier, a second rectifier and a stator rectifying unit. Wherein, stator rectification unit contains rectifier ring and go-between, the rectifier ring contains along axial fore-and-aft distribution's first rectifier ring and second rectifier ring, the go-between is connected first rectifier ring with between the second rectifier ring, every the rectifier ring is the two segmentation structures of dividing equally half in its circumference. The first rectifier is connected to the first rectifier ring. The outer wall of second rectifier is provided with a plurality of first recesses of looks spaced along circumference, the rear end of the inner wall of second rectifier ring is provided with a plurality of first bosss of looks spaced along circumference, the second rectifier ring passes through first boss with the cooperation of first recess connect in the second rectifier. The front end of the inner wall of second rectifier ring is provided with a plurality of second bosss of looks spaced along circumference, the rear end of the inner wall of first rectifier ring is provided with a plurality of third bosss of looks spaced along circumference, the rear end of the outer wall of go-between is provided with a plurality of second recesses of looks spaced along circumference, and the front end is provided with a plurality of third recesses of looks spaced along circumference, the go-between ring passes through the second boss with the cooperation of second recess connect in second rectifier ring, the go-between passes through the third boss with the cooperation of third recess connect in first rectifier ring.
According to one embodiment of the invention, the rectifier ring further comprises at least one third rectifier ring, each third rectifier ring is sequentially distributed between the first rectifier ring and the second rectifier ring along the axial direction, and the connecting ring is connected between every two adjacent rectifier rings.
According to yet another aspect of the present invention, a compressor is provided that includes a stator rectifier ring structure. The stator rectifying ring structure is the stator rectifying ring structure proposed by the present invention and described in the above embodiments.
According to a further aspect of the invention, there is provided an aircraft engine comprising a compressor. Wherein the compressor is the compressor proposed by the present invention and described in the above embodiments.
According to the technical scheme, the stator rectifier ring structure, the air compressor and the aircraft engine have the advantages and positive effects that:
the stator rectifying ring structure provided by the invention is a two-section structure with half and half equal distribution in the circumferential direction of the rectifying ring. The rear end of the first rectifier is connected to the rectifier ring. The outer wall of the front end of second rectifier is provided with a plurality of first recesses of looks spaced along circumference, and the inner wall of the rear end of rectifier ring is provided with a plurality of first bosss of looks spaced along circumference, and the rectifier ring is connected in the second rectifier through the cooperation of first boss and first recess. Through the design, the stator rectifying ring structure provided by the invention adopts a half-half equal rectifying ring structure, does not need to additionally arrange a half-dividing casing, and is suitable for installation and positioning of a multifunctional integrated stator guide vane ring. In addition, the invention realizes the axial positioning of the rectifier ring and the rectifier by utilizing the design of the multi-section boss and the groove, and simultaneously can realize the function of preventing the rectifier ring and the rectifier from rotating relatively in the circumferential direction. Therefore, the pneumatic valve is convenient to repeatedly assemble and disassemble, high in working reliability and small in pneumatic leakage.
Drawings
Various objects, features and advantages of the present invention will become more apparent from the following detailed description of preferred embodiments of the invention, when considered in conjunction with the accompanying drawings. The drawings are merely exemplary of the invention and are not necessarily drawn to scale. In the drawings, like reference characters designate the same or similar parts throughout the different views. Wherein:
FIG. 1 is a partial cross-sectional view of a stator rectifier ring structure shown in accordance with an exemplary embodiment;
FIG. 2 is a partial perspective view of the stator rectifier ring structure shown in FIG. 1;
FIG. 3 is an assembled schematic view of the stator rectifier ring structure shown in FIG. 1;
FIG. 4 is a cross-sectional view taken along line A-A of FIG. 3;
FIG. 5 is a partial cross-sectional view of a stator rectifier ring structure shown in accordance with another exemplary embodiment.
The reference numerals are explained below:
100. a first rectifier;
110. a first inner annular surface;
120. a second inner annular surface;
200. a second rectifier;
210. a groove;
220. a seal ring;
230. a sealing groove;
240. a first groove;
300. a rectifying ring;
310. a boss;
320. a first outer annular surface;
330. a second outer annulus;
500. a second rectifier ring;
510. a first boss;
520. a second boss;
600. a connecting ring;
610. a second groove;
620. a third groove;
700. a third rectifier ring;
710. a fourth boss;
720. and a fifth boss.
Detailed Description
Exemplary embodiments that embody features and advantages of the invention are described in detail below. It is to be understood that the invention is capable of other and different embodiments and its several details are capable of modification without departing from the scope of the invention, and that the description and drawings are accordingly to be regarded as illustrative in nature and not as restrictive.
In the following description of various exemplary embodiments of the invention, reference is made to the accompanying drawings, which form a part hereof, and in which are shown by way of illustration various exemplary structures, systems, and steps in which aspects of the invention may be practiced. It is to be understood that other specific arrangements of parts, structures, example devices, systems, and steps may be utilized and structural and functional modifications may be made without departing from the scope of the present invention. Moreover, although the terms "over," "between," "within," and the like may be used in this specification to describe various example features and elements of the invention, these terms are used herein for convenience only, e.g., in accordance with the orientation of the examples described in the figures. Nothing in this specification should be construed as requiring a specific three dimensional orientation of structures in order to fall within the scope of the invention.
Referring to fig. 1, there is representatively illustrated a partial cross-sectional view of a stator rectifier ring structure in accordance with the present invention. In the exemplary embodiment, the stator commutating ring structure proposed by the present invention is described by taking the application to a compressor as an example. Those skilled in the art will readily appreciate that various modifications, additions, substitutions, deletions, or other changes may be made to the specific embodiments described below in order to apply the inventive concepts of the stator fairing configuration to other types of engine configurations or other applications, and still fall within the scope of the principles of the stator fairing configuration set forth herein.
As shown in fig. 1, in the present embodiment, the stator rectifying ring structure provided by the present invention at least includes a first rectifier 100, a second rectifier 200, and a stator rectifying unit, and the stator rectifying unit includes a rectifying ring 300. Referring to fig. 2-4 in combination, fig. 2 representatively illustrates a partial perspective view of a stator rectifier ring structure; an assembly schematic of a stator rectifier ring structure is representatively illustrated in fig. 3; a cross-sectional view taken along line a-a of fig. 3 is representatively illustrated in fig. 4. The structure, connection mode and functional relationship of the main components of the stator commutator ring structure proposed by the present invention will be described in detail below with reference to the drawings.
As shown in fig. 1 to 4, in the present embodiment, the rectifier ring 300 has a two-stage structure divided into halves in the circumferential direction. For example, the rectifier ring 300 of the full ring structure may be cut into two half ring structures along the radial direction thereof, and the two half ring structures are preferably both in a semi-circular arc shape. The rear end of the first rectifier 100 is connected to the rectifier ring 300, and the first rectifier 100 can press and center the rectifier ring 300. The outer wall of the front end of the second rectifier 200 is provided with a plurality of grooves 210, and the grooves 210 are sequentially distributed at intervals in the circumferential direction of the second rectifier 200. The inner wall of the rear end of the fairing 300 is provided with a plurality of bosses 310, and the bosses 310 are sequentially distributed at intervals along the circumferential direction of the fairing 300. The positions of the plurality of grooves 210 and the plurality of bosses 310 correspond to each other one by one, so that the rectifier ring 300 can be connected with the second rectifier 200 through the cooperation of the bosses 310 and the grooves 210. Through the design, the stator rectifying ring structure provided by the invention adopts a half-half equal rectifying ring 300 structure, does not need to additionally arrange a half-dividing casing, and is suitable for installation and positioning of a multifunctional integrated stator guide vane ring. In addition, the design of the multi-section boss 310 and the groove 210 is utilized, the axial positioning of the rectifying ring 300 and the rectifier is realized, and the effect of preventing the rectifying ring 300 and the rectifier from rotating circumferentially relatively is realized, so that the compact and reliable assembling requirement can be met. In addition, the inner wall of the rectifying ring 300 is still provided with the boss 310 in the inner ring surface (inner cylindrical surface), so that the primary centering function can be performed on the overlapped object (for example, the second rectifier 200). The invention has higher structure compactness, and does not need to adopt bolts except for the force transmission starting point and the force transmission terminal. Therefore, the pneumatic valve is convenient to repeatedly assemble and disassemble, high in working reliability and small in pneumatic leakage.
Preferably, as shown in fig. 1, in the present embodiment, the connection relationship between the first rectifier 100 and the rectifier ring 300 may be preferably that an inner wall of the rear end of the first rectifier 100 is sleeved on an outer wall of the rectifier ring 300.
Further, as shown in fig. 1, based on the design that the inner wall of the rear end of the first rectifier 100 is sleeved on the outer wall of the rectifier ring 300, in the present embodiment, the outer wall of the rectifier ring 300 may preferably have two outer annular surfaces, namely, a first outer annular surface 320 and a second outer annular surface 330, and the two outer annular surfaces are distributed along the axial direction of the rectifier ring 300. Of the two outer annular surfaces, the corresponding radius of the first, relatively forward outer annular surface 320 is smaller than the corresponding radius of the second, relatively rearward outer annular surface 330. On this basis, the inner wall of the rear end of the first rectifier 100 may preferably have two inner ring surfaces, i.e., the first inner ring surface 110 and the second inner ring surface 120, and the two inner ring surfaces are distributed to correspond to the two outer ring surfaces, i.e., the first inner ring surface 110 corresponds to the first outer ring surface 320, and the second inner ring surface 120 corresponds to the second outer ring surface 330. Accordingly, when the first rectifier 100 is connected to the rectifier ring 300, that is, when the rear end of the first rectifier 100 is sleeved on the outer circumference of the rectifier ring 300, the two inner ring surfaces are pressed against the two outer ring surfaces, respectively. Through the above design, the first rectifier 100 can utilize the matching design of the two inner ring surfaces and the two outer ring surfaces to realize the centering of the rectifier ring 300 (i.e., to ensure the reliability of other functional structures, such as the labyrinth seal of the rectifier ring 300), and at the same time, can realize the compressing of two semi-circular structures of the rectifier ring 300 with a half-and-half uniform structure into a full circle.
Further, as shown in fig. 1, based on the design that the inner wall of the rear end of the first rectifier 100 is sleeved on the outer wall of the rectifier ring 300, in the present embodiment, a sealing ring 220 may be preferably disposed between the inner wall of the rear end of the first rectifier 100 and the outer wall of the rectifier ring 300.
Further, as shown in fig. 1, based on the design of the sealing ring 220, in the present embodiment, the outer wall of the rectifier ring 300 may preferably be provided with a sealing groove 230, and the sealing groove 230 is provided on the outer wall of the rectifier ring 300 along the circumferential direction. Accordingly, the sealing ring 220 is disposed in the sealing groove 230, and forms a seal between the sealing groove 230 of the rectifier ring 300 and the inner wall of the first rectifier 100.
Preferably, in the present embodiment, the lengths of the bosses 310 in the circumferential direction of the fairing ring 300 may preferably be all equal, and the plurality of bosses 310 may preferably be evenly distributed at intervals in the circumferential direction of the fairing ring 300. Correspondingly, the lengths of the respective grooves 210 in the circumferential direction of the second commutator 200 may preferably be all equal, and the plurality of grooves 210 may preferably be evenly spaced in the circumferential direction of the second commutator 200. Through the design, in the connecting operation of the rectifier ring 300 and the second rectifier 200, each boss 310 and the groove 210 do not need to be aligned, so that the adjustment and alignment of the rectifier ring 300 and the second rectifier 200 in the circumferential direction in the operation process are simplified, and the installation process is further simplified.
As shown in fig. 5, which representatively illustrates a partial cross-sectional view of a stator rectifier ring structure in another embodiment of the present invention. In this second embodiment, the stator commutating ring structure proposed by the present invention is substantially the same as that in the first embodiment shown in fig. 1 to 4. The design of the stator rectifier ring structure in this second embodiment that differs from the first embodiment will be explained below with reference to fig. 1 to 5.
In this embodiment, the stator rectifying unit includes a rectifying ring and a connecting ring, and the rectifying ring may include at least a first rectifying ring and a second rectifying ring. Specifically, the first fairing ring and the second fairing ring are distributed front and back along the axial direction. The connecting ring is connected between the first rectifying ring and the second rectifying ring. Each rectifying ring is still in a two-section structure with half and half equally divided in the circumferential direction. The first rectifier is connected to the first rectifier ring. The outer wall of the second rectifier is provided with a plurality of first grooves which are sequentially distributed at intervals along the circumferential direction of the second rectifier. The rear end of the inner wall of the second rectifying ring is provided with a plurality of first bosses which are distributed at intervals along the circumferential direction of the second rectifying ring. The positions of the first grooves and the first bosses are in one-to-one correspondence, so that the second rectifier ring can be connected with the second rectifier through the matching of the first bosses and the first grooves. The front end of the inner wall of the second rectifying ring is provided with a plurality of second bosses which are sequentially distributed at intervals along the circumferential direction of the second rectifying ring. The rear end of the inner wall of the first rectifying ring is provided with a plurality of third bosses which are sequentially distributed at intervals along the circumferential direction of the first rectifying ring. The rear end of the outer wall of the connecting ring is provided with a plurality of second grooves which are sequentially distributed at intervals along the circumferential direction of the connecting ring. The front end of the outer wall of the connecting ring is provided with a plurality of third grooves which are sequentially distributed at intervals along the circumferential direction of the connecting ring. The positions of the second grooves and the second bosses are in one-to-one correspondence, so that the connecting ring can be connected to the second rectifying ring through the matching of the second bosses and the second grooves. The third grooves correspond to the third bosses in position one to one, so that the connecting ring can be connected to the first rectifying ring through the matching of the third bosses and the third grooves. Through the design, the stator rectifier ring structure provided by the invention can realize modular expansion of the structure on the basis of the first embodiment, namely, the arrangement of a multi-stage rectifier ring is realized by utilizing the connecting ring, and the expansion of multi-stage application is realized. Simultaneously, because the adoption is along the cooperation structure realization both of circumference interval distribution's a plurality of pairs of recess and boss between go-between and the rectifier ring is connected, consequently in this second embodiment, not only the connection structure of rectifier ring and rectifier, still include the connection structure between the adjacent rectifier ring, the homoenergetic is when realizing rectifier ring and rectifier axial positioning, realizes preventing the effect of rectifier ring and the relative circumferential direction of rectifier. In addition, in the embodiment, each stage of rectifying ring has high independence, so that the rectifying rings are half-cut and installed conveniently, and the adjacent two stages of rectifying rings are connected by the adapter ring with the whole ring structure, so that interstage pneumatic leakage can be further reduced, and interstage sealing is facilitated.
Preferably, in this embodiment, the rectifier ring of the stator rectifier unit may further preferably include at least one third rectifier ring, the third rectifier rings are axially distributed between the first rectifier ring and the second rectifier ring in sequence, and a connection ring is connected between every two adjacent rectifier rings (including the first rectifier ring, the second rectifier ring and the at least one third rectifier ring). Specifically, as shown in fig. 5, taking the case that the commutator ring of the stator commutator ring structure includes a third commutator ring 700, the stator commutator ring structure includes two connecting rings. Wherein, a go-between is connected between first rectifier ring and third rectifier ring 700, the rear end of the inner wall of first rectifier ring is provided with the boss, the front end of the outer wall of this go-between 600 is provided with matched with recess, the front end of the inner wall of third rectifier ring 700 is provided with the boss (be the fourth boss 710), the rear end of the outer wall of this go-between 600 also is provided with matched with recess, and above-mentioned boss and recess all can preferably adopt the multistage formula design along circumference interval distribution, in view of the above, the front end and the rear end of this go-between 600 are connected respectively between the rear end of first rectifier ring and the front end of third rectifier ring 700 through the cooperation of above-mentioned boss and recess. Similarly, another connection ring 600 is connected between the second rectifier ring 500 and the third rectifier ring 700, a boss is provided at the front end of the inner wall of the second rectifier ring 500, a matching groove is provided at the rear end of the outer wall of the another connection ring 600, a boss (i.e., the fifth boss 720) is provided at the rear end of the inner wall of the third rectifier ring 700, a matching groove (i.e., the third groove 620) is also provided at the front end of the outer wall of the another connection ring 600, and both the boss and the groove may preferably be designed in a multi-stage manner distributed at intervals in the circumferential direction, and accordingly, the front end and the rear end of the another connection ring 600 are respectively connected between the rear end of the third rectifier ring 700 and the front end of the second rectifier ring 500 through the matching of the boss and the groove. In addition, the rear end of the outer wall of the another connection ring 600 is provided with the above-mentioned second groove 610, and the second groove 610 is engaged with the second boss 520 of the front end of the inner wall of the second fairing ring 500. In other embodiments, when the rectifying ring of the stator rectifying unit includes a plurality of third rectifying rings 700, a structure similar to the above design may also be adopted, which is not described herein again.
It should be noted that, since the rectifiers, the rectifier rings and the connecting rings are designed to have substantially the same axial direction, in this specification, the axial direction of each rectifier ring and the axial direction of the connecting ring are understood to be the same axial direction, that is, the axial direction of the stator rectifier ring structure. The circumferential direction of each commutator, the circumferential direction of the commutator ring, and the circumferential direction of the connecting ring can be understood as a plurality of circumferential directions parallel to each other in the axial direction in the space, that is, the circumferential direction of the stator commutator ring structure. In addition, the direction from the first rectifier to the second rectifier is defined as a front-to-back direction, so that one end of each rectifying ring close to the first rectifier is a front end, and the other end of each rectifying ring close to the second rectifier is a back end.
It should be noted herein that the stator rectifier ring structures illustrated in the drawings and described in this specification are only a few examples of the wide variety of stator rectifier ring structures that the principles of the present invention can be employed in. It should be clearly understood that the principles of the present invention are in no way limited to any of the details of the stator rectifier ring structure or any of the components of the stator rectifier ring structure shown in the drawings or described in this specification.
Based on the above detailed description of several exemplary embodiments of the stator commutating ring structure proposed by the present invention, an embodiment of the compressor proposed by the present invention will be described below.
In this embodiment, the compressor proposed by the present invention comprises at least a stator commutating ring structure. The stator commutating ring structure proposed by the present invention and described in detail in the above embodiments is used.
It should be noted herein that the compressors shown in the drawings and described in this specification are only a few examples of the many types of compressors that can employ the principles of the present invention. It should be clearly understood that the principles of the present invention are in no way limited to any of the details of the compressor or any of the components of the compressor shown in the drawings or described in this specification.
Based on the above description of several exemplary embodiments of the stator fairing structure and compressor proposed by the present invention, one embodiment of the aircraft engine proposed by the present invention will be described below.
In the embodiment, the aircraft engine provided by the invention at least comprises a compressor. The compressor is the one proposed by the present invention and described in the above embodiments.
It should be noted herein that the aircraft engines illustrated in the figures and described in the present specification are but a few examples of the wide variety of aircraft engines that can employ the principles of the present invention. It should be clearly understood that the principles of this invention are in no way limited to any of the details of the aircraft engine or any of the components of the aircraft engine shown in the drawings or described in this specification.
In summary, the stator rectifying ring structure of the present invention has a two-stage structure with the rectifying ring divided into two halves in the circumferential direction. The rear end of the first rectifier is connected to the rectifier ring. The outer wall of the front end of second rectifier is provided with a plurality of first recesses of looks spaced along circumference, and the inner wall of the rear end of rectifier ring is provided with a plurality of first bosss of looks spaced along circumference, and the rectifier ring is connected in the second rectifier through the cooperation of first boss and first recess. Through the design, the stator rectifying ring structure provided by the invention adopts a half-half equal rectifying ring structure, does not need to additionally arrange a half-dividing casing, and is suitable for installation and positioning of a multifunctional integrated stator guide vane ring. In addition, the invention realizes the axial positioning of the rectifier ring and the rectifier by utilizing the design of the multi-section boss and the groove, and simultaneously can realize the function of preventing the rectifier ring and the rectifier from rotating relatively in the circumferential direction. Therefore, the stator rectifier ring structure provided by the invention is convenient to repeatedly assemble and disassemble, high in working reliability and small in pneumatic leakage.
Exemplary embodiments of the stator fairing ring construction, compressor and aircraft engine set forth in the present disclosure are described and/or illustrated in detail above. Embodiments of the invention are not limited to the specific embodiments described herein, but rather, components and/or steps of each embodiment may be utilized independently and separately from other components and/or steps described herein. Each component and/or step of one embodiment can also be used in combination with other components and/or steps of other embodiments. When introducing elements/components/etc. described and/or illustrated herein, the articles "a," "an," and "the" are intended to mean that there are one or more of the elements/components/etc. The terms "comprising," "including," and "having" are intended to be inclusive and mean that there may be additional elements/components/etc. other than the listed elements/components/etc. Furthermore, the terms "first", "second", and "third", etc. in the claims and the description are used merely as labels, and are not numerical limitations of their objects.
While the stator fairing configuration, compressor and aircraft engine presented herein have been described in terms of various specific embodiments, those skilled in the art will recognize that the invention can be practiced with modification within the spirit and scope of the claims.
Claims (8)
1. A stator rectifying ring structure comprises a first rectifier, a second rectifier and a stator rectifying unit; the method is characterized in that:
the stator rectifying unit comprises a rectifying ring, and the rectifying ring is of a two-section structure which is divided into half parts in the circumferential direction;
the rear end of the first rectifier is connected to the rectifying ring and used for compressing and centering the rectifying ring;
the outer wall of the front end of second rectifier is provided with a plurality of recesses of looks spaced along circumference, the inner wall of the rear end of rectifier ring is provided with a plurality of bosss of looks spaced along circumference, the rectifier ring passes through the boss with the cooperation of recess connect in the second rectifier.
2. The stator rectifier ring structure of claim 1 wherein the inner wall of the aft end of the first rectifier is nested within the outer wall of the rectifier ring.
3. The stator fairing ring structure of claim 2, wherein said outer wall of said fairing ring has two outer annular surfaces, said two outer annular surfaces being axially spaced, the corresponding radius of the forward facing outer annular surface being less than the corresponding radius of the other outer annular surface; the inner wall of the rear end of the first rectifier is provided with two inner ring surfaces, and when the first rectifier is connected to the rectifying ring, the two inner ring surfaces are respectively pressed against the two outer ring surfaces.
4. The stator rectifier ring structure of claim 2 wherein the back end of the first rectifier extends rearward and is nested outside of the second rectifier; and a sealing ring is arranged between the inner wall of the first rectifier and the outer wall of the second rectifier.
5. The stator rectifying ring structure defined in claim 4 wherein the outer wall of the second rectifier has a sealing groove formed along the circumferential direction thereof, and the sealing ring is disposed in the sealing groove.
6. The stator fairing ring structure of claim 1 wherein each of said lands is of equal length in the circumferential direction and a plurality of said lands are evenly spaced in the circumferential direction; the lengths of the grooves in the circumferential direction are equal, and the grooves are uniformly distributed at intervals in the circumferential direction.
7. An air compressor comprising a stator fairing ring structure, wherein the stator fairing ring structure is as claimed in any one of claims 1 to 6.
8. An aircraft engine comprising a compressor, wherein the compressor is according to claim 7.
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| CN202010313582.4A CN111486129B (en) | 2020-04-20 | 2020-04-20 | Stator rectifier ring structure, compressor and aircraft engine |
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| CN202010313582.4A CN111486129B (en) | 2020-04-20 | 2020-04-20 | Stator rectifier ring structure, compressor and aircraft engine |
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| FR2859509B1 (en) * | 2003-09-10 | 2006-01-13 | Snecma Moteurs | ROTATION STOP OF AUBES AREAS OF RECTIFIERS BY BARRETTES IN THE SEAL PLANS OF THE CARTER |
| FR2878293B1 (en) * | 2004-11-24 | 2009-08-21 | Snecma Moteurs Sa | MOUNTING DISTRIBUTOR SECTIONS IN AXIAL COMPRESSOR |
| FR2961553B1 (en) * | 2010-06-18 | 2012-08-31 | Snecma | ANGULAR RECTIFIER SECTOR FOR TURBOMACHINE COMPRESSOR, TURBOMACHINE RECTIFIER AND TURBOMACHINE COMPRISING SUCH A SECTOR |
| JP2012172575A (en) * | 2011-02-21 | 2012-09-10 | Ihi Corp | Stator vane cascade |
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