CN214091970U - Turbine integral blade disc - Google Patents
Turbine integral blade disc Download PDFInfo
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- CN214091970U CN214091970U CN202023329045.3U CN202023329045U CN214091970U CN 214091970 U CN214091970 U CN 214091970U CN 202023329045 U CN202023329045 U CN 202023329045U CN 214091970 U CN214091970 U CN 214091970U
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Abstract
The application discloses a turbine blisk, wherein a first annular cavity, a second annular cavity and a third annular cavity are arranged on the turbine blisk; the first annular cavity extends from the rotating shaft part to the connecting part at a position close to the exhaust end and forms a closed curved surface; the second annular cavity extends from the rotating shaft part to the connecting part at a position close to the air inlet end and forms a closed curved surface; the third annular cavity is positioned in the edge part and forms a closed curved surface. By adopting the technical scheme, compared with a solid turbine blisk, the solid turbine blisk has lower mass and can meet the stress requirement.
Description
Technical Field
The application relates to the field of aircraft engines, in particular to a turbine blisk.
Background
The turbine blisk is a key part of an aircraft engine, and the quality of the turbine blisk has very important influence on the performance of the aircraft engine. Under the condition of ensuring that the stress of the turbine blisk meets the allowable material stress, the weight of the turbine blisk is reduced, the weight of an aircraft engine can be reduced, the utilization rate of materials is improved, and the thrust-weight ratio of the engine is improved. Whereas prior art turbine blisks are generally solid. FIG. 1 illustrates a typical turbine blisk 10' rotating about a first axis and having an inlet end located below FIG. 1 and an exhaust end located above FIG. 1. Fig. 2 shows the structure of a turbine blisk 10' comprising a turbine disk 1 and several blades 2 integral with each other; each blade 2 is arranged on the periphery of the turbine disk 1. The turbine disk 1 includes a rotating shaft portion 11, a connecting portion 12, a disk body portion 13, and an edge portion 14, which are integrally connected to each other, in this order from inside to outside in a radial direction. Wherein, the rotating shaft part 11 is provided with a shaft hole along the first shaft direction. The connecting portion 12 connects the rotating shaft portion 11 and the disk portion 13 while tapering radially from inside to outside. The rim portion 14 is formed by the disk portion 13 tapering radially from the inside to the outside. Fig. 3 shows the stress distribution of the turbine blisk 10'.
SUMMERY OF THE UTILITY MODEL
It is an object of the present application to overcome the above-described deficiencies or problems in the background and to provide a turbine blisk that has lower mass than a solid turbine blisk and that is capable of meeting stress requirements.
In order to achieve the purpose, the following technical scheme is adopted:
a turbine blisk rotates about a first axis and is provided with an inlet end and an exhaust end; it includes: the turbine disc and the blades are connected into a whole; each blade is arranged on the periphery of the turbine disc; the turbine disc sequentially comprises a rotating shaft part, a connecting part, a disc body part and an edge part which are connected into a whole from inside to outside along the radial direction; the rotating shaft part is provided with a shaft hole along the first shaft direction; the connecting part connects the rotating shaft part and the disc body part in a gradually reducing manner from inside to outside along the radial direction; the edge part is formed by gradually expanding the disc body part from inside to outside along the radial direction; the turbine disc is provided with a first annular cavity, a second annular cavity and a third annular cavity; the first annular cavity extends from the rotating shaft part to the connecting part at a position close to the exhaust end and forms a closed curved surface; the second annular cavity extends from the rotating shaft part to the connecting part at a position close to the air inlet end and forms a closed curved surface; the third annular cavity is positioned in the edge part and forms a closed curved surface.
In a preferred embodiment, a closed curve formed on the meridian section by the first ring cavity is formed by enclosing a first straight line section, a second straight line section, a third straight line section, a fourth straight line section, a fifth straight line section and a sixth straight line section in sequence, and adjacent straight line sections are connected through smooth transition; the first straight line segment is positioned in the rotating shaft part and inclines to the air inlet end from inside to outside along the radial direction; the second straight line section is positioned in the rotating shaft part and is parallel to the first shaft, and one end of the second straight line section, which is close to the exhaust end, is connected with one end of the first straight line section, which is close to the air inlet end; the third straight line section extends from the rotating shaft part to the connecting part and inclines to the air inlet end from inside to outside along the radial direction; the fourth straight line section is positioned in the connecting part and inclines to the air inlet end from outside to inside along the radial direction; the fifth straight line segment extends from the connecting part to the rotating shaft part and inclines towards the exhaust end from outside to inside along the radial direction; the sixth straight line section is positioned in the rotating shaft part and is parallel to the first shaft.
Furthermore, a closed curve formed on the meridian section by the second annular cavity is formed by sequentially enclosing a seventh straight line segment, an eighth straight line segment, a ninth straight line segment, a tenth straight line segment, an eleventh straight line segment and a first circular arc line segment, and adjacent line segments are connected through smooth transition; the seventh straight line segment is positioned in the rotating shaft part and is parallel to the first shaft; the eighth straight line segment extends from the rotating shaft part to the connecting part and inclines to the exhaust end from inside to outside along the radial direction, and one end of the eighth straight line segment, which is close to the shaft hole, is connected with one end of the seventh straight line segment, which is close to the exhaust end; the ninth straight line segment is positioned in the connecting part and inclines to the air inlet end from inside to outside along the radial direction; the tenth straight line section extends from the connecting part to the rotating shaft part and inclines towards the air inlet end from outside to inside along the radial direction; the eleventh straight line segment is positioned in the rotating shaft part and is parallel to the first shaft.
Furthermore, a closed curve formed on the meridian section by the third annular cavity is formed by enclosing a twelfth straight line segment, a thirteenth straight line segment and a fourteenth straight line segment in sequence, and adjacent straight line segments are connected through smooth transition; the twelfth straight line segment is inclined to the exhaust end from inside to outside along the radial direction; the thirteenth straight line section inclines towards the air inlet end from inside to outside along the radial direction, and one end, close to the air outlet end, of the thirteenth straight line section is connected with one end, close to the air outlet end, of the twelfth straight line section; the fourteenth straight section is inclined to the exhaust end from outside to inside in the radial direction.
Further, the first, third, eighth, ninth, twelfth and thirteenth linear segments do not include more than 45 ° from the first axis.
In another preferred embodiment, a closed curve formed on the meridian section of the first annular cavity is formed by enclosing a fifteenth straight line segment, a sixteenth straight line segment, a seventeenth straight line segment, an eighteenth straight line segment, a nineteenth straight line segment and a twentieth straight line segment in sequence, and adjacent straight line segments are connected through smooth transition; the fifteenth straight line segment is positioned in the rotating shaft part and is vertical to the first shaft; the sixteenth straight line section is positioned in the rotating shaft part and is parallel to the first shaft, and one end, close to the exhaust end, of the sixteenth straight line section is connected with one end, far away from the shaft hole, of the fifteenth straight line section; the seventeenth straight line section extends from the rotating shaft part to the connecting part and inclines towards the air inlet end from inside to outside along the radial direction; the eighteenth straight line section is positioned in the connecting part and inclines to the air inlet end from outside to inside along the radial direction; the nineteenth straight line segment extends from the connecting part to the rotating shaft part and inclines to the exhaust end from outside to inside along the radial direction; the twentieth straight-line segment is positioned in the rotating shaft part and is parallel to the first shaft.
Furthermore, a closed curve formed on the meridian section by the second annular cavity is formed by sequentially enclosing a twenty-first straight line section, a twenty-second straight line section, a twenty-third straight line section, a twenty-fourth straight line section, a twenty-fifth straight line section and a second circular arc line section, and adjacent line sections are connected through smooth transition; the twenty-first straight line segment is positioned in the rotating shaft part and is parallel to the first shaft; the twenty-second straight line section extends from the rotating shaft part to the connecting part and inclines towards the exhaust end from inside to outside along the radial direction, and one end of the twenty-second straight line section, which is close to the shaft hole, is connected with one end of the twenty-first straight line section, which is close to the exhaust end; the twenty-third straight line segment is positioned in the connecting part and inclines to the air inlet end from inside to outside along the radial direction; the twenty-fourth straight line segment extends from the connecting part to the rotating shaft part and inclines towards the air inlet end from outside to inside along the radial direction; the twenty-fifth straight line segment is positioned in the rotating shaft part and is parallel to the first shaft.
Further, the closed curve formed by the third annular cavity on the meridional section is an ellipse, and the long axis of the closed curve is perpendicular to the first axis.
Compared with the prior art, the scheme has the following beneficial effects:
according to the turbine blisk, the closed cavity is formed in the area with smaller internal stress of the turbine disk. In the application, because pivot portion and connecting portion are less in the position stress of being close to exhaust end and inlet end, consequently set up first annular chamber and second annular chamber respectively in pivot portion and connecting portion near the position of exhaust end and inlet end to reach and subtract heavy purpose. At the edge part, the wall thickness of the turbine disk is thicker, and the strength redundancy is higher, so that the third annular cavity is arranged, and the weight reduction purpose is achieved.
Drawings
In order to more clearly illustrate the technical solution of the embodiments, the drawings needed to be used are briefly described as follows:
FIG. 1 is a perspective view of a prior art turbine blisk;
FIG. 2 is a cross-sectional view of a prior art turbine blisk;
FIG. 3 is a prior art stress distribution map across a turbine blisk meridional section;
FIG. 4 is a meridional section of a turbine blisk in accordance with a first embodiment;
FIG. 5 is a turbine blisk meridian section in accordance with a second embodiment.
Detailed Description
In the claims and specification, unless otherwise specified the terms "first", "second" or "third", etc., are used to distinguish between different items and are not used to describe a particular order.
In the claims and specification, unless otherwise specified, the terms "central," "lateral," "longitudinal," "horizontal," "vertical," "top," "bottom," "inner," "outer," "upper," "lower," "front," "rear," "left," "right," "clockwise," "counterclockwise," and the like are used in the orientation and positional relationship indicated in the drawings and are used for ease of description only and do not imply that the referenced device or element must have a particular orientation or be constructed and operated in a particular orientation.
In the claims and the specification, unless otherwise defined, the terms "fixedly" or "fixedly connected" are to be understood in a broad sense as meaning any connection which is not in a relative rotational or translational relationship, i.e. including non-detachably fixed connection, integrally connected and fixedly connected by other means or elements.
In the claims and specification, unless otherwise defined, the terms "comprising", "having" and variations thereof mean "including but not limited to".
In the claims and in the description, unless otherwise specified, the term "tapered radially from the inside to the outside" means that the connecting portion is inclined in the direction from the inside to the outside in the radial direction, the outer surface close to the exhaust end being inclined in the direction of the intake end, and the outer surface close to the intake end being inclined in the direction of the exhaust end.
In the claims and the description, unless otherwise specified, the term "tapering radially from the inside to the outside" means that the edge portion is inclined in the direction from the inside to the outside in the radial direction, the outer surface near the discharge end being inclined in the direction of the discharge end, and the outer surface near the intake end being inclined in the direction of the intake end.
In the claims and in the description, unless otherwise specified, the term "meridional section" means a section taken on one of the two sides of the central axis of the radial section.
The technical solution in the embodiments will be clearly and completely described below with reference to the accompanying drawings.
Example one
Referring to fig. 4, fig. 4 shows a turbine blisk 10 in a first embodiment. As shown in fig. 4, the turbine blisk 10 of the present embodiment is an improvement of the turbine blisk 10 'of the prior art, and is different from the turbine blisk 10' of the prior art in that a first annular chamber 3, a second annular chamber 4, and a third annular chamber 5 are provided in the turbine disk 1.
Wherein, the first annular cavity 3 extends from the rotating shaft part 11 to the connecting part 12 at a position close to the exhaust end and forms a closed curved surface. The closed curve formed by the first ring cavity 3 on the meridian section is formed by enclosing a first straight line segment S01, a second straight line segment S02, a third straight line segment S03, a fourth straight line segment S04, a fifth straight line segment S05 and a sixth straight line segment S06 in sequence, and all the straight line segments are connected through smooth transition. Wherein a first straight line segment S01 is located inside the rotating shaft portion 11, and is inclined from inside to outside in the radial direction toward the air intake end; the second straight line segment S02 is positioned in the rotating shaft part 11 and is parallel to the first shaft, and one end of the second straight line segment S02 close to the exhaust end is connected with one end of the first straight line segment S01 close to the air inlet end; the third straight line segment S03 extends from the rotating shaft portion 11 to the connecting portion 12, and is inclined from inside to outside in the radial direction toward the air inlet end; the fourth straight line segment S04 is positioned in the connecting part and inclines towards the air inlet end from outside to inside along the radial direction; the fifth straight line segment S05 extends from the connecting portion 12 to the rotating shaft portion 11, and is inclined toward the exhaust end from the outside to the inside in the radial direction; the sixth straight line segment S06 is located inside the rotating shaft portion 11, and is parallel to the first axis. Wherein the first straight line segment S01 and the third straight line segment S03 form an included angle of not more than 45 degrees with the first axis.
The second annular chamber 4 extends from the spindle portion 11 to the connecting portion 12 at a position near the intake end and forms a closed curved surface. A closed curve formed on the meridian section of the second annular cavity 4 is formed by sequentially enclosing a seventh straight line segment S07, an eighth straight line segment S08, a ninth straight line segment S09, a tenth straight line segment S10, an eleventh straight line segment S11 and a first circular arc segment A01, and adjacent line segments are connected through smooth transition; the seventh straight line segment S07 is positioned in the rotating shaft part 11 and is parallel to the first shaft; the eighth straight line segment S08 extends from the rotating shaft part 11 to the connecting part 12 and inclines from inside to outside to the exhaust end along the radial direction, and one end of the eighth straight line segment S08 close to the shaft hole is connected with one end of the seventh straight line segment S07 close to the exhaust end; the ninth straight line segment S09 is positioned in the connecting part 12 and inclines from inside to outside along the radial direction to the air inlet end; the tenth straight line segment S10 extends from the connecting portion 12 to the rotating shaft portion 11 and is inclined radially from the outside to the inside toward the intake end; the eleventh straight line segment S11 is located inside the rotating shaft portion 11 and is parallel to the first shaft. Wherein the angle between the eighth straight line segment S08 and the ninth straight line segment S09 and the first axis is not more than 45 degrees.
The third annular chamber 5 is located within the rim portion 14 and forms a closed curve. The third ring cavity 5 forms a closed curve on a meridian section, the closed curve is formed by enclosing a twelfth straight line segment S12, a thirteenth straight line segment S13 and a fourteenth straight line segment S14 in sequence, and adjacent straight line segments are connected through smooth transition; the segment of the twelfth straight line S12 is inclined from inside to outside to the exhaust end along the radial direction; the thirteenth straight line segment S13 inclines from inside to outside along the radial direction to the air inlet end, and one end of the thirteenth straight line segment S13 close to the air outlet end is connected with one end of the twelfth straight line segment S12 close to the air outlet end; the fourteenth straight line S14 is inclined radially from outside to inside towards the exhaust end. Wherein the included angle between the twelfth straight line segment S12 and the thirteenth straight line segment S13 and the first axis is not more than 45 degrees.
The turbine blisk 10 of the present embodiment is manufactured in a 3D printed material stack. Wherein the first annular chamber 3, the second annular chamber 4 and the third annular chamber 5 are all located in areas where stress is not concentrated, and therefore the reduction in strength is within an allowable range. By providing the first annular chamber 3, the second annular chamber 4 and the third annular chamber 5, the mass of the turbine blisk 10 is reduced by 14.79% compared to the prior art turbine blisk 10'.
Example two
Referring to fig. 5, fig. 5 shows a turbine blisk 10 in a second embodiment. As shown in fig. 5, the turbine blisk 10 of the present embodiment is an improvement of the turbine blisk 10 'of the prior art, and is different from the turbine blisk 10' of the prior art in that a first annular chamber 3, a second annular chamber 4, and a third annular chamber 5 are provided in the turbine disk 1.
Wherein, the first annular cavity 3 extends from the rotating shaft part 11 to the connecting part 12 at a position close to the exhaust end and forms a closed curved surface. The first ring cavity 3 is formed by a closed curve on a meridian section, which is formed by a fifteenth straight line segment S15, a sixteenth straight line segment S16, a seventeenth straight line segment S17, an eighteenth straight line segment S18, a nineteenth straight line segment S19 and a twentieth straight line segment S20 in sequence, and adjacent straight line segments are connected through smooth transition; the fifteenth straight line segment S15 is located inside the rotating shaft part 11 and is perpendicular to the first shaft; the sixteenth straight line segment S16 is positioned in the rotating shaft part 11 and is parallel to the first shaft, and one end of the sixteenth straight line segment S16, which is close to the exhaust end, is connected with one end of the fifteenth straight line segment S15, which is far away from the shaft hole; the seventeenth straight line segment S17 extends from the rotating shaft portion 11 to the connecting portion 12 and inclines from inside to outside in the radial direction to the air inlet end; the eighteenth straight line segment S18 is positioned in the connecting part 12 and inclines towards the air inlet end from outside to inside along the radial direction; the nineteenth straight line segment S19 extends from the connecting part 12 to the rotating shaft part 11 and inclines to the exhaust end from outside to inside along the radial direction; the twentieth straight line segment S20 is located inside the rotating shaft portion and is parallel to the first shaft.
The second annular chamber 4 extends from the spindle portion 11 to the connecting portion 12 at a position near the intake end and forms a closed curved surface. A closed curve formed on the meridian section of the second annular cavity 4 is formed by sequentially enclosing a twenty-first straight line segment S21, a twenty-second straight line segment S22, a twenty-third straight line segment S23, a twenty-fourth straight line segment S24, a twenty-fifth straight line segment S25 and a second circular arc segment A02, and adjacent line segments are connected through smooth transition; the twenty-first straight line segment S21 is positioned in the rotating shaft part 11 and is parallel to the first shaft; the twenty-second straight line segment S22 extends from the rotating shaft part 11 to the connecting part 12 and inclines to the exhaust end from inside to outside along the radial direction, and one end of the twenty-second straight line segment S22 close to the shaft hole is connected with one end of the twenty-first straight line segment S21 close to the exhaust end; the twenty-third straight line segment S23 is positioned in the connecting part 12 and inclines from inside to outside along the radial direction to the air inlet end; the twenty-fourth straight line segment S24 extends from the connecting portion 12 to the rotating shaft portion 11 and inclines radially from the outside to the inside toward the intake end; the twenty-fifth straight line segment S25 is located inside the spindle portion 11 and is parallel to the first axis.
The third annular chamber 5 is located within the rim portion 14 and forms a closed curve. The closed curve E01, formed by the third annular chamber 5 in a meridional section, is elliptical with its major axis perpendicular to the first axis.
The turbine blisk 10 of the present embodiment is not limited by the inclination angle of the 3D printed material stack. Wherein the first annular chamber 3, the second annular chamber 4 and the third annular chamber 5 are all located in areas where stress is not concentrated, and therefore the reduction in strength is within an allowable range. By providing the first annular chamber 3, the second annular chamber 4 and the third annular chamber 5, the mass of the turbine blisk 10 is reduced by 16.06% compared to the prior art turbine blisk 10'.
The description of the above specification and examples is intended to be illustrative of the scope of the present application and is not intended to be limiting.
Claims (8)
1. A turbine blisk rotates about a first axis and is provided with an inlet end and an exhaust end; it includes: the turbine disc and the blades are connected into a whole; each blade is arranged on the periphery of the turbine disc; the turbine disc sequentially comprises a rotating shaft part, a connecting part, a disc body part and an edge part which are connected into a whole from inside to outside along the radial direction; the rotating shaft part is provided with a shaft hole along the first shaft direction; the connecting part connects the rotating shaft part and the disc body part in a gradually reducing manner from inside to outside along the radial direction; the edge part is formed by gradually expanding the disc body part from inside to outside along the radial direction; the turbine disc is characterized in that the turbine disc is provided with a first annular cavity, a second annular cavity and a third annular cavity; the first annular cavity extends from the rotating shaft part to the connecting part at a position close to the exhaust end and forms a closed curved surface; the second annular cavity extends from the rotating shaft part to the connecting part at a position close to the air inlet end and forms a closed curved surface; the third annular cavity is positioned in the edge part and forms a closed curved surface.
2. The turbine blisk according to claim 1, wherein a closed curve formed by the first annular cavity on the meridian section is formed by enclosing a first straight line segment, a second straight line segment, a third straight line segment, a fourth straight line segment, a fifth straight line segment and a sixth straight line segment in sequence, and adjacent straight line segments are connected through smooth transition; the first straight line segment is positioned in the rotating shaft part and inclines to the air inlet end from inside to outside along the radial direction; the second straight line section is positioned in the rotating shaft part and is parallel to the first shaft, and one end of the second straight line section, which is close to the exhaust end, is connected with one end of the first straight line section, which is close to the air inlet end; the third straight line section extends from the rotating shaft part to the connecting part and inclines to the air inlet end from inside to outside along the radial direction; the fourth straight line section is positioned in the connecting part and inclines to the air inlet end from outside to inside along the radial direction; the fifth straight line segment extends from the connecting part to the rotating shaft part and inclines towards the exhaust end from outside to inside along the radial direction; the sixth straight line section is positioned in the rotating shaft part and is parallel to the first shaft.
3. The turbine blisk according to claim 2, wherein a closed curve formed by the second annular cavity on the meridian section is formed by enclosing a seventh straight line segment, an eighth straight line segment, a ninth straight line segment, a tenth straight line segment, an eleventh straight line segment and a first circular arc line segment in sequence, and adjacent line segments are connected through smooth transition; the seventh straight line segment is positioned in the rotating shaft part and is parallel to the first shaft; the eighth straight line segment extends from the rotating shaft part to the connecting part and inclines to the exhaust end from inside to outside along the radial direction, and one end of the eighth straight line segment, which is close to the shaft hole, is connected with one end of the seventh straight line segment, which is close to the exhaust end; the ninth straight line segment is positioned in the connecting part and inclines to the air inlet end from inside to outside along the radial direction; the tenth straight line section extends from the connecting part to the rotating shaft part and inclines towards the air inlet end from outside to inside along the radial direction; the eleventh straight line segment is positioned in the rotating shaft part and is parallel to the first shaft.
4. The turbine blisk according to claim 3, wherein the third annular cavity forms a closed curve on a meridian cross section, which is formed by enclosing a twelfth straight line segment, a thirteenth straight line segment and a fourteenth straight line segment in sequence, and adjacent straight line segments are connected through smooth transition; the twelfth straight line segment is inclined to the exhaust end from inside to outside along the radial direction; the thirteenth straight line section inclines towards the air inlet end from inside to outside along the radial direction, and one end, close to the air outlet end, of the thirteenth straight line section is connected with one end, close to the air outlet end, of the twelfth straight line section; the fourteenth straight section is inclined to the exhaust end from outside to inside in the radial direction.
5. The turbine blisk in accordance with claim 4 wherein said first linear segment, said third linear segment, said eighth linear segment, said ninth linear segment, said twelfth linear segment and said thirteenth linear segment form an angle of no more than 45 ° with respect to said first axis.
6. The turbine blisk according to claim 1, wherein a closed curve formed by the first toroidal cavity on the meridian section is formed by sequentially enclosing a fifteenth straight-line segment, a sixteenth straight-line segment, a seventeenth straight-line segment, an eighteenth straight-line segment, a nineteenth straight-line segment and a twentieth straight-line segment, and adjacent straight-line segments are connected through smooth transition; the fifteenth straight line segment is positioned in the rotating shaft part and is vertical to the first shaft; the sixteenth straight line section is positioned in the rotating shaft part and is parallel to the first shaft, and one end, close to the exhaust end, of the sixteenth straight line section is connected with one end, far away from the shaft hole, of the fifteenth straight line section; the seventeenth straight line section extends from the rotating shaft part to the connecting part and inclines towards the air inlet end from inside to outside along the radial direction; the eighteenth straight line section is positioned in the connecting part and inclines to the air inlet end from outside to inside along the radial direction; the nineteenth straight line segment extends from the connecting part to the rotating shaft part and inclines to the exhaust end from outside to inside along the radial direction; the twentieth straight-line segment is positioned in the rotating shaft part and is parallel to the first shaft.
7. The turbine blisk according to claim 6, wherein a closed curve formed by the second annular cavity on the meridian section is formed by enclosing a twenty-first straight line segment, a twenty-second straight line segment, a twenty-third straight line segment, a twenty-fourth straight line segment, a twenty-fifth straight line segment and a second circular arc line segment in sequence, and adjacent line segments are connected through smooth transition; the twenty-first straight line segment is positioned in the rotating shaft part and is parallel to the first shaft; the twenty-second straight line section extends from the rotating shaft part to the connecting part and inclines towards the exhaust end from inside to outside along the radial direction, and one end of the twenty-second straight line section, which is close to the shaft hole, is connected with one end of the twenty-first straight line section, which is close to the exhaust end; the twenty-third straight line segment is positioned in the connecting part and inclines to the air inlet end from inside to outside along the radial direction; the twenty-fourth straight line segment extends from the connecting part to the rotating shaft part and inclines towards the air inlet end from outside to inside along the radial direction; the twenty-fifth straight line segment is positioned in the rotating shaft part and is parallel to the first shaft.
8. A turbine blisk in accordance with claim 7, wherein said third annular cavity defines a closed curve in meridional cross-section having an elliptical shape with a major axis perpendicular to said first axis.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023329045.3U CN214091970U (en) | 2020-12-30 | 2020-12-30 | Turbine integral blade disc |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023329045.3U CN214091970U (en) | 2020-12-30 | 2020-12-30 | Turbine integral blade disc |
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| Publication Number | Publication Date |
|---|---|
| CN214091970U true CN214091970U (en) | 2021-08-31 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202023329045.3U Active CN214091970U (en) | 2020-12-30 | 2020-12-30 | Turbine integral blade disc |
Country Status (1)
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|---|---|
| CN (1) | CN214091970U (en) |
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- 2020-12-30 CN CN202023329045.3U patent/CN214091970U/en active Active
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