CN114734208B - Integral blade ring structure of oblique flow or centrifugal impeller and machining method thereof - Google Patents
Integral blade ring structure of oblique flow or centrifugal impeller and machining method thereof Download PDFInfo
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Abstract
The invention discloses a monolithic vane ring structure of an oblique flow or centrifugal impeller and a processing method thereof, belonging to the field of design of an aircraft engine compressor. According to the structural characteristics that the outer diameter of a wheel disc of an oblique flow or centrifugal impeller is gradually increased from an inlet to an outlet, the composite material in the impeller is laid and axially divided into a plurality of areas, in order to ensure that the filament breakage rate is low and the laying shape is not deformed in the hot isostatic pressing process, a single area is firstly and independently laid for hot isostatic pressing forming, then a plurality of areas are combined and the outer ring blank of a blade part is sleeved with the outer ring blank for hot isostatic pressing forming again, finally, an oblique flow or centrifugal impeller integral blade ring blank is formed, and then the oblique flow or centrifugal impeller integral blade ring structure is obtained through machining. Compared with a pure alloy blade disc, the integral blade ring made of the fiber reinforced composite material can raise the lowest radius of the wheel disc and reduce the weight.
Description
Technical Field
The invention belongs to the technical field of manufacturing of an aircraft engine compressor impeller, relates to an oblique flow or centrifugal impeller structure and a processing method thereof, and particularly relates to an integral vane ring structure of an oblique flow or centrifugal impeller and a processing method thereof.
Background
With the development demand of high-performance and high thrust-weight ratio of the aero-engine, the weight reduction demand of the engine is more and more urgent. The high thrust-weight ratio engine has increasingly strict requirements on the weight indexes of all parts, and in order to realize the high-requirement weight indexes, the adoption of a new process of a new material of a new structure becomes an important means for reducing the weight of all parts. The compression part is one of three major parts of an aircraft engine, and the reduction of the weight of the compression part plays an important role in improving the thrust-weight ratio of the engine. For this reason, in addition to the improvement of the compression member design method, further development of more advanced lightweight high-performance materials and lightweight structural members is required.
Generally, for an impeller, fan blades are fixedly arranged on a wheel disc in a tenon root or mortise connection structure mode, on one hand, the tenon root or mortise connection structure has certain weight, the wheel disc needs a rim with enough thickness for supporting the quality, the connection structure also enables the number of engine parts to be large, and on the other hand, certain pneumatic loss and fretting wear can be caused when airflow flows in a gap between the tenon root and the mortise. For the weight that alleviates above-mentioned traditional impeller structure, developed impeller blisk and integral blade ring structure among the prior art, the blisk is the structure of making blade and rim plate as an organic whole, saves conventional tenon and the tongue-and-groove of dish connection night, has alleviateed the quality of impeller greatly, has also promoted aerodynamic performance to a certain extent simultaneously. Compared with a blisk structure, the blisk technology has a better weight reduction effect, a wheel disc part in the blisk is removed to form the blisk, and the blisk is lack of a wheel disc bearing load and cannot bear the centrifugal load of blades, so that the blisk can only be made of composite materials with lower density, and the weight of the blisk made of the composite materials is about 30% -70% of that of a conventional structure.
The existing machining and manufacturing technology of the integral vane ring is mainly applied to axial-flow impellers, but is less applied to oblique-flow or centrifugal impellers, the main reason is that the radius drop of an inner flow passage of the oblique-flow or centrifugal impeller from an inlet to an outlet is large, so that the outer diameter of a wheel disc of the oblique-flow or centrifugal impeller is gradually increased from the inlet to the outlet, the structural characteristics of the oblique-flow or centrifugal impeller enable the shape of a composite material in the vane ring to be different from that of a vane disc of an axial-flow compressor, the structural characteristics also make it difficult to directly apply the integral vane ring structural technology of the axial-flow impeller to the oblique-flow or centrifugal impeller, and the reason is that the main flow of the existing oblique-flow or centrifugal impeller still adopts pure alloy type vane discs, so that the lowest radius of the wheel disc is small, and the weight is large. How to use the integral blade ring structure technology of the axial flow impeller for reference so as to reduce the weight of the oblique flow or centrifugal impeller is a technical problem to be solved urgently in the field of machining and manufacturing of the oblique flow or centrifugal impeller.
Disclosure of Invention
In order to ensure that the filament breakage rate is low and the laying shape is not deformed in the hot isostatic pressing process, the single block area is selected to be independently laid for hot isostatic pressing forming, then the outer ring blanks of the blade parts which are combined and sleeved in the multiple areas are subjected to hot isostatic pressing forming again, finally the oblique flow or centrifugal impeller integral blade ring blank is formed, and then the oblique flow or centrifugal impeller integral blade ring structure is obtained through machining. Compared with pure alloy blade discs, the integral blade ring made of the fiber reinforced composite material can raise the minimum radius of the wheel disc and reduce the weight.
In order to solve the technical problem, the invention adopts the technical scheme that:
a method for machining a blisk ring of an oblique flow or centrifugal impeller, characterized in that it comprises at least the following steps:
SS1, respectively processing and manufacturing a blade outer ring blank and a wheel disc blank according to the design size of a target oblique flow or centrifugal impeller integral blade ring, wherein the blade outer ring blank is of an integral structure and comprises a plurality of mutually independent wheel disc sub-blanks, and the blade outer ring blank and each wheel disc sub-blank are processed by alloy forging, wherein,
according to the design size of a wheel disc of a target diagonal flow or centrifugal impeller integral vane ring, dividing the wheel disc blank into a plurality of independent wheel disc blanks in a plurality of areas along the axial direction according to different heights of the wheel disc, wherein each wheel disc blank is an annular columnar part with a regular shape, a composite material filling ring groove is machined in each wheel disc blank on the side surface of the wheel disc blank, the axial width of each composite material filling ring groove is the same or gradually decreases along the direction from the inlet to the outlet of the wheel disc, and the radial height gradually increases along the direction from the inlet to the outlet of the wheel disc; each composite material filling ring groove is correspondingly processed with an annular cover-shaped component used for sealing the composite material filling ring groove; the composite material filling ring groove is used for filling an annular composite material prefabricated part, the composite material prefabricated part is covered by an annular cover-shaped part after being filled into the composite material filling ring groove, and hot isostatic pressing consolidation is carried out to enable the wheel disc blank, the composite material prefabricated part and the annular cover-shaped part to be compounded into a whole;
the blade outer ring blank is integrally an annular columnar part, and stepped holes matched with the shape and size of each wheel disc blank are sequentially machined in the inner hole of the blade outer ring blank from a wheel disc inlet to a wheel disc outlet along the axial direction;
SS2, after each wheel plate blank and the composite material preform are subjected to hot isostatic pressing composite forming, each wheel plate blank is respectively placed into a step hole corresponding to the blade outer ring blank and is subjected to hot isostatic pressing composite with the blade outer ring blank again to form a whole, and finally, a whole oblique flow or centrifugal impeller whole blade ring blank is formed;
and SS3, processing the integral oblique flow or centrifugal impeller integral vane ring blank according to the design size of the target oblique flow or centrifugal impeller integral vane ring to obtain the target oblique flow or centrifugal impeller integral vane ring.
Preferably, in step SS1, the axial width of each wheel disc blank is the same or gradually decreases along the direction from the wheel disc inlet to the wheel disc outlet, and the radial height gradually increases along the direction from the wheel disc inlet to the wheel disc outlet.
Preferably, in step SS1, the base material of the blade outer ring blank and the wheel disc blank is titanium alloy, titanium-aluminum alloy or high-temperature alloy, correspondingly, the composite material preform is made of SiC fiber reinforced titanium-based, titanium-aluminum-based or high-temperature alloy-based composite material, and the metal material wrapped by the outer layer of the composite material SiC fiber wire is the same as the base material of the disc body blank.
Further, for the impeller with lower working temperature, siC fiber reinforced titanium-based composite material is adopted; for the impeller with high temperature at the working temperature, siC fiber reinforced titanium-aluminum alloy based composite material is adopted; for the impeller with higher temperature, siC fiber reinforced high-temperature alloy matrix composite material is adopted.
Preferably, in step SS1 above, the wheel disc blank is divided into 3 or more regions of individual wheel disc blanks in the axial direction from the inlet to the outlet of the wheel disc.
Preferably, in the step SS2, after the step holes corresponding to the blade outer ring blanks are placed into the step holes, the axial side surfaces of the wheel plate blanks are tightly attached to each other.
Preferably, in step SS3, the integral oblique flow or centrifugal impeller blisk blank is machined to a depth that is spaced from each composite material-filled ring groove to avoid damage to the composite material.
Another object of the present invention is to provide a mixed flow or centrifugal impeller blisk prepared by the above method.
Compared with the prior art, the integral vane ring structure of the oblique flow or centrifugal impeller and the processing method thereof have the advantages that according to the structural characteristics that the outer diameter of the wheel disc of the oblique flow or centrifugal impeller gradually rises from an inlet to an outlet, the stress characteristics and the design requirements of the oblique flow or centrifugal impeller, the composite material in the impeller is laid and axially divided into a plurality of areas, in order to ensure that the filament breakage rate is low and the laying shape is not deformed in the hot isostatic pressing process, hot isostatic pressing forming is selected to be independently laid according to a single area, then the outer ring blanks of the blade parts which are combined and sleeved in the plurality of areas are subjected to hot isostatic pressing forming again, finally, the integral vane ring blank of the oblique flow or centrifugal impeller is formed, and then the integral vane ring structure of the oblique flow or centrifugal impeller is obtained through machining. Compared with pure alloy blade discs, the integral blade ring made of the fiber reinforced composite material can raise the minimum radius of the wheel disc and reduce the weight. The oblique flow or centrifugal impeller integral vane ring is not only suitable for reducing the weight of a common oblique flow or centrifugal impeller wheel disc, but also suitable for an oblique flow or centrifugal impeller wheel disc fixed by a central pull rod, and avoids the situation that the central pull rod is too thin and not stable enough or machining is difficult due to the excessively low radius of the inner ring of the wheel disc. The invention can also be applied directly to diagonal flow or centrifugal impellers requiring reduced weight or requiring greater bore space.
Drawings
FIG. 1 is a schematic view of a diagonal flow impeller blisk structure according to the present invention;
FIG. 2 is a schematic view of the centrifugal impeller integral vane ring structure of the present invention;
FIG. 3 is a sectional view of a diagonal flow impeller blisk blank preparation section according to the present invention;
FIG. 4 is a sectional view of a centrifugal impeller blisk blank of the present invention.
Description of reference numerals:
the wind guide blade comprises wind guide blades 1, main blades 2, an impeller wheel disc 3, a composite material I area 4, a composite material II area 5, a composite material III area 6, a wheel disc blank I7, a wheel disc blank II 8, a wheel disc blank III 9 and a blade outer ring blank 10.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments, which are part of the present invention, are not all embodiments, and are intended to be illustrative of the present invention and should not be construed as limiting the present invention. All other embodiments, which can be obtained by a person skilled in the art without inventive step based on the embodiments of the present invention, are within the scope of protection of the present invention.
As shown in fig. 3 and 4, the method for machining a vane ring of an oblique flow or centrifugal impeller of the present invention mainly includes the following steps:
SS1, respectively processing and manufacturing a blade outer ring blank 10 and a wheel disc blank according to the design size of a target diagonal flow or centrifugal impeller integral vane ring, wherein the blade outer ring blank 10 is of an integral structure, the wheel disc blank comprises a plurality of mutually independent wheel disc blanks, the figure shows that the wheel disc blank I7, the wheel disc blank II 8 and the wheel disc blank III 9 are formed by forging and processing alloy, the wheel disc blank 10 and the wheel disc blanks I-III 7, 8 and 9 are formed by axially dividing the wheel disc blank into a plurality of regions according to the design size of the wheel disc of the target diagonal flow or centrifugal impeller integral vane ring, the wheel disc blanks I-III 7, 8 and 9 are all annular columnar parts with regular shapes, composite material filling ring grooves are processed on the side surfaces of the wheel disc blanks I-III 7, 8 and 9 according to the different heights of the wheel disc, the axial widths of the composite material filling ring grooves are the same or are gradually reduced along the direction from the wheel disc inlet to the outlet, and the radial height of the composite material filling ring grooves are gradually increased along the direction from the wheel disc inlet to the wheel disc outlet; each composite material filling ring groove is correspondingly processed with an annular cover-shaped component for sealing the composite material filling ring groove; the composite material filling ring groove is used for filling an annular composite material prefabricated body, the composite material prefabricated body is covered by an annular cover-shaped part after being filled into the composite material filling ring groove, and hot isostatic pressing consolidation is carried out to enable the wheel disc blank, the composite material prefabricated body and the annular cover-shaped part to be compounded into a whole; the blade outer ring blank 10 is an annular cylindrical part as a whole, and stepped holes matched with the shapes and sizes of the wheel disc sub-blanks I-III 7, 8 and 9 are sequentially processed in the inner hole of the blade outer ring blank from the wheel disc inlet to the wheel disc outlet along the axial direction.
When the step SS1 is implemented, preferably, the axial widths of the roughcasts I to III 7, 8 and 9 of the wheel discs are the same or gradually decrease along the direction from the inlet to the outlet of the wheel discs, and the radial heights of the roughcasts are gradually increased along the direction from the inlet to the outlet of the wheel discs. The base materials of the blade outer ring blank and the wheel disc blank are titanium alloy, titanium-aluminum alloy or high-temperature alloy, correspondingly, the composite material preform adopts SiC fiber reinforced titanium base, titanium-aluminum base or high-temperature alloy base composite material, and the metal material wrapped by the outer layer of the SiC fiber wire of the composite material is the same as the base material of the wheel disc blank. For the impeller with lower working temperature, siC fiber reinforced titanium-based composite material is adopted; for the impeller with high temperature at the working temperature, siC fiber reinforced titanium-aluminum alloy based composite material is adopted; for the impeller with higher temperature, siC fiber reinforced high-temperature alloy matrix composite material is adopted. The wheel disc blank is preferably divided into 3 or more regions of individual wheel disc blanks in the axial direction from the inlet to the outlet of the wheel disc.
And SS2, after the wheel disc blanks I to III 7, 8 and 9 are respectively subjected to hot isostatic pressing composite forming with the composite material prefabricated body, respectively putting the wheel disc blanks into step holes corresponding to the blade outer ring blank 10, and carrying out hot isostatic pressing composite with the blade outer ring blank 10 to form a whole, and finally forming a whole oblique flow or centrifugal impeller whole blade ring blank. When the step SS2 is implemented, preferably, after the step SS is placed into the step hole corresponding to the blade outer ring blank 10, the axial side faces of the wheel disc sub-blanks I to III 7, 8 and 9 are tightly attached.
And SS3, processing the integral oblique flow or centrifugal impeller integral vane ring blank according to the design size of the target oblique flow or centrifugal impeller integral vane ring to obtain the target oblique flow or centrifugal impeller integral vane ring. When the step SS3 is implemented, preferably, the integral oblique flow or centrifugal impeller integral vane ring blank is processed, and the processing depth keeps a certain distance from each composite material filling ring groove so as to avoid damaging the composite material.
Fig. 1 and 2 show a diagonal flow impeller or centrifugal impeller blisk manufactured by the method of the present invention, where fig. 1 is a schematic structural view of the diagonal flow impeller blisk, and fig. 2 is a schematic structural view of the centrifugal impeller blisk. The change of the radius value of the flow channel in the inlet and the outlet of the oblique flow or centrifugal impeller is large, so that the difference of the height values of the impeller wheel discs from the inlet to the outlet is large when the inner diameter values of the impeller wheel discs 3 are the same, and further, the composite material needs to be paved in a subarea mode. Taking fig. 1 and 2 as an example, the composite material is laid in three areas from the inlet to the outlet of the impeller disc according to different heights of the impeller disc, namely a composite material area I4, a composite material area II 5 and a composite material area III 6. The blank of the integral vane ring of the oblique flow or centrifugal impeller is prepared by independently laying hot isostatic pressing according to a single block area and then carrying out hot isostatic pressing on the outer ring blanks of three combined sleeved blade parts. Specifically, the wheel disc sub-blank I7, the wheel disc sub-blank II 8 and the wheel disc sub-blank III 9 are separately formed in different regions, and after the respective forming, the blade outer ring blank 10 is added, namely, the impeller blade part blank is formed by hot isostatic pressing again. Finally, an integral oblique flow or centrifugal impeller integral vane ring blank is formed, and then an oblique flow or centrifugal impeller integral vane ring structure is obtained through machining.
The object of the present invention is fully effectively achieved by the above embodiments. Those skilled in the art will appreciate that the present invention includes, but is not limited to, what is described in the accompanying drawings and the foregoing detailed description. While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications within the spirit and scope of the appended claims.
The invention has not been described in detail and is part of the common general knowledge of a person skilled in the art.
Claims (6)
1. A method for machining a blisk ring of an oblique flow or centrifugal impeller, characterized in that it comprises at least the following steps:
SS1, respectively processing and manufacturing a blade outer ring blank and a wheel disc blank according to the design size of a target oblique flow or centrifugal impeller integral blade ring, wherein the blade outer ring blank is of an integral structure, the wheel disc blank comprises a plurality of mutually independent wheel disc sub-blanks, and the blade outer ring blank and each wheel disc sub-blank are processed by alloy forging, wherein,
according to the design size of a wheel disc of a target diagonal flow or centrifugal impeller integral vane ring, dividing the wheel disc blank into a plurality of independent wheel disc blanks in a plurality of areas along the axial direction according to different heights of the wheel disc, wherein each wheel disc blank is an annular columnar part with a regular shape, a composite material filling ring groove is machined in each wheel disc blank on the side surface of the wheel disc blank, the axial width of each composite material filling ring groove is the same or gradually decreases along the direction from the inlet to the outlet of the wheel disc, and the radial height gradually increases along the direction from the inlet to the outlet of the wheel disc; each composite material filling ring groove is correspondingly processed with an annular cover-shaped component used for sealing the composite material filling ring groove; the composite material filling ring groove is used for filling an annular composite material prefabricated part, the composite material prefabricated part is covered by an annular cover-shaped part after being filled into the composite material filling ring groove, and hot isostatic pressing consolidation is carried out to enable the wheel disc blank, the composite material prefabricated part and the annular cover-shaped part to be compounded into a whole;
the blade outer ring blank is integrally an annular columnar part, and stepped holes matched with the shape and size of each wheel disc blank are sequentially machined in the inner hole of the blade outer ring blank from a wheel disc inlet to a wheel disc outlet along the axial direction;
SS2, after each wheel plate blank and the composite material preform are subjected to hot isostatic pressing composite forming, each wheel plate blank is respectively placed into a step hole corresponding to the blade outer ring blank and is subjected to hot isostatic pressing composite with the blade outer ring blank again to form a whole, and finally, a whole oblique flow or centrifugal impeller whole blade ring blank is formed;
and SS3, processing the integral oblique flow or centrifugal impeller integral vane ring blank according to the design size of the target oblique flow or centrifugal impeller integral vane ring to obtain the target oblique flow or centrifugal impeller integral vane ring.
2. The method of claim 1, wherein in step SS1, the axial width of each of the disk blanks is the same or gradually decreases along the direction from the disk entrance to the disk exit, and the radial height of each of the disk blanks gradually increases along the direction from the disk entrance to the disk exit.
3. The method of claim 1 wherein in step SS1, said wheel disc blank is divided into a plurality of regions of individual wheel disc blanks in the axial direction from the wheel disc inlet to the wheel disc outlet.
4. The method as claimed in claim 1, wherein in step SS2, the axial side of each wheel disk blank is tightly attached to the axial side of the wheel disk blank after the blade outer ring blank is placed into the corresponding stepped hole.
5. The method of claim 1 wherein step SS3 is performed by machining a single-piece, diagonal flow or centrifugal impeller blisk blank to a depth spaced from each composite material-filled ring groove to avoid damage to the composite material.
6. A diagonal flow or centrifugal impeller blisk prepared by the method of any of claims 1 to 5.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210402974.7A CN114734208B (en) | 2022-04-18 | 2022-04-18 | Integral blade ring structure of oblique flow or centrifugal impeller and machining method thereof |
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| CN202210402974.7A CN114734208B (en) | 2022-04-18 | 2022-04-18 | Integral blade ring structure of oblique flow or centrifugal impeller and machining method thereof |
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| CN114734208B true CN114734208B (en) | 2023-03-03 |
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