CN114263632A - Rotor component of engine fan - Google Patents
Rotor component of engine fan Download PDFInfo
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- CN114263632A CN114263632A CN202111234960.0A CN202111234960A CN114263632A CN 114263632 A CN114263632 A CN 114263632A CN 202111234960 A CN202111234960 A CN 202111234960A CN 114263632 A CN114263632 A CN 114263632A
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Abstract
The application belongs to the technical field of aeroengine fan rotor part design, concretely relates to engine fan rotor part, include: the multiple drums are provided with multiple oil throwing holes distributed along the circumferential direction; the adjacent two stages of rotor discs are connected through a drum barrel; the multistage rotor blade, the rotor blade of each grade before the last stage rotor blade and the rotor rim plate of corresponding level are connected through the dish tenon structure, and last stage rotor blade integrated into one piece is on last stage rotor rim plate.
Description
Technical Field
The application belongs to the technical field of aeroengine fan rotor part design, concretely relates to engine fan rotor part.
Background
Currently, the following two main structural forms exist for the rotor part of the engine fan:
1) the fan rotor blades and the rotor wheel disc at all levels are connected by adopting a disc tenon structure, and the fan rotor blades and the rotor wheel disc at all levels are connected by the structure, so that a large number of connecting pieces are required, the integral quality of a rotor part of a fan of an engine is increased, the requirement on weight reduction of the engine is not met, the structure is complex, and the processing and the assembly are difficult;
2) the fan rotor blades and the rotor wheel discs in the structural forms are long in production and processing period and high in price, and the fan rotor blades and the rotor wheel discs need to be integrally replaced after being damaged, so that the maintenance is difficult.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without clear evidence that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an engine fan rotor component which overcomes or mitigates at least one of the technical disadvantages of the known prior art.
The technical scheme of the application is as follows:
an engine fan rotor component comprising:
the multiple drums are provided with multiple oil throwing holes distributed along the circumferential direction;
the adjacent two stages of rotor discs are connected through a drum barrel;
the multistage rotor blade, the rotor blade of each grade before the last stage rotor blade and the rotor rim plate of corresponding level are connected through the dish tenon structure, and last stage rotor blade integrated into one piece is on last stage rotor rim plate.
According to at least one embodiment of the present application, in the above-mentioned rotor component of the engine fan, the front end of each drum is connected with the rear edge of the corresponding preceding rotor disk by bolts;
the rear end of each drum barrel is integrally formed on the front edge part of the corresponding rear-stage rotor disc.
According to at least one embodiment of the present application, in the above-mentioned rotor component of the engine fan, the outer edge portion of each stage of rotor disk before the last stage of rotor disk is provided with a plurality of dovetail-shaped mortises extending along the axial direction;
the root of each stage of rotor blade before the last stage of rotor blade is provided with a dovetail tenon; the dovetail tenons of all levels are clamped into the dovetail mortises of the corresponding levels.
According to at least one embodiment of the present application, in the above-mentioned rotor component of the engine fan, one end of each stage dovetail-shaped mortise extends to a front edge portion of the corresponding stage rotor disk to form a notch.
According to at least one embodiment of the present application, in the above-mentioned engine fan rotor component, the leading edge portion of each stage of rotor disk before the last stage of rotor disk has a plurality of leading edge protruded portions; the inner side of the protruding part of the front edge of each stage is provided with a clamping groove;
the engine fan rotor component further comprising:
and the check rings are correspondingly clamped in the first-stage clamping grooves to shield the notches of the corresponding stages.
According to at least one embodiment of the present application, the above-mentioned rotor part of the engine fan further comprises:
the first-stage counterweight nails are screwed on the front edge part of the first-stage rotor disc along the circumferential direction;
and each first-stage locking plate is correspondingly padded between the front edge parts of one first-stage counterweight nail and the first-stage rotor wheel disc.
According to at least one embodiment of the present application, in the above-mentioned engine fan rotor component, the trailing edge portion of the last stage rotor disk has a trailing edge annular bulge; the inner side of the annular protruding part of the rear edge is provided with an annular counterweight groove;
the engine fan rotor component further comprising:
a plurality of last-stage connecting bolts;
the last-stage balancing weights are distributed in the annular balancing groove along the circumferential direction; each final-stage balancing weight is correspondingly screwed on the annular convex part at the rear edge through a final-stage connecting bolt;
and each last-stage locking plate is correspondingly padded between one last-stage connecting bolt and the rear edge of the annular convex part of the rear edge.
According to at least one embodiment of the present application, there are two drums in the above-described rotor assembly of the engine fan;
the rotor disk and the rotor blades have three stages.
Drawings
FIG. 1 is a schematic illustration of an engine fan rotor assembly provided by an embodiment of the present application;
wherein:
1-a drum; 2-a rotor disk; 3-rotor blades; 4-a retainer ring; 5-first level counterweight nail; 6-first stage locking plate; 7-last level connecting bolt; 8-the final stage of balancing weight; 9-last stage locking plate.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; furthermore, the drawings are for illustrative purposes, and the terms used to describe the positional relationships are merely exemplary in nature and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
Furthermore, unless otherwise defined, technical terms or disciplines used in the description of the present application should be given their ordinary meanings as understood by those of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientation, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only and to distinguish between various components and are not to be construed as indicating or implying any relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The use of the terms "comprising" or "including" in the description of the present application is intended to indicate that an element or item appearing before the term is intended to cover the element or item listed after the term and its equivalents, without excluding other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1.
An engine fan rotor component comprising:
the drum type oil slinging device comprises a plurality of drum drums 1, wherein each drum 1 is provided with a plurality of oil slinging holes distributed along the circumferential direction;
the multistage rotor disk 2 is characterized in that adjacent two stages of rotor disks 1 are connected through a drum 2;
the multistage rotor blade 3, rotor blade 3 and the rotor disk 2 of the corresponding level of the rotor blade 3 at different levels before the last stage of rotor blade 3 are connected through the disc tenon structure, and the last stage of rotor blade 3 is integrated into one piece on the last stage of rotor disk 1.
For the engine fan rotor part disclosed in the above embodiment, a person skilled in the art can understand that, in the engine fan rotor part, the last stage rotor disk 2 and the rotor blades 3 thereof are relatively difficult to damage, the last stage rotor disk 2 and the rotor blades 3 thereof are designed to be an integrated structure, the overall quality of the engine fan rotor part can be reduced to a certain extent, the processing and assembling difficulty is reduced, the rotor blades 3 at all stages before the last stage rotor blade 3 are designed to be connected with the corresponding stage rotor disk 2 through a disk tenon structure, when damage occurs, only the damaged part is replaced, the maintenance is convenient, and the manufacturing cost is low.
For the engine fan rotor component disclosed in the above embodiment, a person skilled in the art can also understand that, aiming at the characteristic that the last stage rotor disk 2 and the rotor blades 3 thereof in the engine fan rotor component are relatively not easy to be damaged, the advantages and disadvantages of structural connection and integral forming of the fan rotor blades and the rotor disk disks are combined, each stage of rotor blades 3 before the last stage of rotor blades 3 are designed to be connected with the corresponding stage of rotor disk 2 through a disk tenon structure, the last stage of rotor blades 3 are integrally formed on the last stage of rotor disk 1, and the requirements of the fan rotor component in various aspects such as weight, processing, assembly, manufacturing cost, maintenance and the like are considered.
With respect to the engine fan rotor member disclosed in the above embodiments, it will also be understood by those skilled in the art that each drum 1 is designed with a plurality of circumferentially distributed oil slinging holes for slinging oil inside the engine fan rotor member.
In some alternative embodiments, in the above-mentioned engine fan rotor component, the front end of each drum 1 is bolted to the rear edge of the corresponding preceding rotor disk 2;
the rear end of each drum 1 is integrally formed on the front edge portion of the corresponding rotor disc 2 at the rear stage thereof.
In some alternative embodiments, in the above-mentioned engine fan rotor component, the outer edge portion of each stage of rotor disk 2 before the last stage of rotor disk 2 has a plurality of dovetail-shaped mortises extending along the axial direction;
the root of each stage of rotor blade 3 before the last stage of rotor blade 3 is provided with a dovetail tenon; the dovetail tenons of all levels are clamped into the dovetail mortises of the corresponding levels.
In some alternative embodiments, one end of each dovetail slot of the above-mentioned engine fan rotor component extends to the leading edge portion of the corresponding rotor disk 2, and a notch is formed, so that each dovetail can be clamped into the corresponding dovetail slot of the corresponding stage.
In some alternative embodiments, in the above-mentioned engine fan rotor component, the leading edge portion of each stage of rotor disk 2 before the last stage of rotor disk 2 has a plurality of leading edge protruded portions; the inner side of the protruding part of the front edge of each stage is provided with a clamping groove;
the engine fan rotor component further comprising:
a plurality of retaining rings 4, every retaining ring 4 corresponds the card in one-level draw-in groove, shelters from the breach of corresponding level to this prevents that the dovetail tenon of corresponding level from deviating from the breach that corresponds, avoids corresponding level's rotor blade 3 to appear not hard up or drop.
In some optional embodiments, the above-mentioned rotor part of the engine fan further comprises:
the first-stage counterweight nails 5 are screwed on the front edge part of the first-stage rotor wheel disc 2 along the circumferential direction;
a plurality of first-stage locking plates 6, and each first-stage locking plate 6 is correspondingly padded between the front edge parts of one first-stage counterweight nail 5 and the first-stage rotor wheel disc 2.
In some alternative embodiments, in the above-mentioned engine fan rotor component, the trailing edge portion of the rotor disc 2 of the last stage has a trailing edge annular bulge; the inner side of the annular convex part of the rear edge is provided with an annular counterweight groove;
the engine fan rotor component further comprising:
a plurality of last-stage connecting bolts 7;
a plurality of final-stage balancing weights 8 are circumferentially distributed in the annular balancing groove; each last-stage weight distribution block 8 is correspondingly screwed on the annular convex part of the rear edge through a last-stage connecting bolt 7;
and a plurality of last-stage locking plates 9, wherein each last-stage locking plate 9 is correspondingly arranged between one last-stage connecting bolt 7 and the rear edge of the rear edge annular protruding part.
In some alternative embodiments, two of the above-described engine fan rotor units are provided as drums 1;
the rotor disk 2 and the rotor blades 3 have three stages.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present invention with reference to the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present invention is not limited to those specific embodiments, and that equivalent modifications or substitutions of the related technical features may be made by those skilled in the art without departing from the principle of the present invention, and those modifications or substitutions will fall within the scope of the present invention.
Claims (8)
1. An engine fan rotor component, comprising:
the oil slinger comprises a plurality of drum drums (1), wherein each drum (1) is provided with a plurality of oil slinger holes distributed along the circumferential direction;
the multistage rotor disk (2), the adjacent two stages of rotor disks (1) are connected through a drum (2);
the rotor disc structure comprises multiple stages of rotor blades (3), wherein each stage of rotor blade (3) before the last stage of rotor blade (3) is connected with a corresponding stage of rotor disc (2) through a disc tenon structure, and the last stage of rotor blade (3) is integrally formed on the last stage of rotor disc (1).
2. An engine fan rotor component according to claim 1,
the front end of each drum barrel (1) is connected with the rear edge of the corresponding preceding-stage rotor disc (2) through bolts;
the rear end of each drum barrel (1) is integrally formed on the front edge part of the corresponding rear-stage rotor disc (2).
3. An engine fan rotor component according to claim 1,
the outer edge part of each stage of rotor disc (2) before the last stage of rotor disc (2) is provided with a plurality of dovetail-shaped mortises extending along the axial direction;
the roots of all stages of rotor blades (3) before the last stage of rotor blade (3) are provided with dovetail-shaped tenons; the dovetail tenons of all levels are clamped into the dovetail mortises of the corresponding levels.
4. An engine fan rotor component according to claim 3,
one end of each stage of dovetail-shaped mortise extends to the front edge part of the corresponding stage of rotor disc (2) to form a notch.
5. An engine fan rotor component according to claim 4,
the front edge part of each stage of rotor disc (2) before the last stage of rotor disc (2) is provided with a plurality of front edge convex parts; the inner side of the protruding part of the front edge of each stage is provided with a clamping groove;
the engine fan rotor component further comprising:
a plurality of retaining rings (4), every retaining ring (4) correspond the card in one-level draw-in groove, shelter from the breach of corresponding level.
6. An engine fan rotor component according to claim 1,
further comprising:
the first-stage counterweight nails (5) are screwed on the front edge part of the first-stage rotor disc (2) along the circumferential direction;
a plurality of first-stage locking plates (6), and each first-stage locking plate (6) corresponds to and fills up between the leading edge position of a first-stage counterweight nail (5), first-stage rotor wheel dish (2).
7. An engine fan rotor component according to claim 1,
the rear edge part of the last stage of rotor disc (2) is provided with a rear edge annular convex part; the inner side of the annular convex part of the rear edge is provided with an annular counterweight groove;
the engine fan rotor component further comprising:
a plurality of last-stage connecting bolts (7);
a plurality of final-stage balancing weights (8) are distributed in the annular balancing groove along the circumferential direction; each final-stage balancing weight (8) is correspondingly screwed on the annular convex part at the rear edge through a final-stage connecting bolt (7);
a plurality of last-stage locking plates (9), wherein each last-stage locking plate (9) is correspondingly padded between one last-stage connecting bolt (7) and the rear edge of the annular convex part of the rear edge.
8. An engine fan rotor component according to claim 1,
the number of the drum barrels (1) is two;
the rotor disk (2) and the rotor blades (3) have three stages.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111234960.0A CN114263632A (en) | 2021-10-22 | 2021-10-22 | Rotor component of engine fan |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111234960.0A CN114263632A (en) | 2021-10-22 | 2021-10-22 | Rotor component of engine fan |
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| Publication Number | Publication Date |
|---|---|
| CN114263632A true CN114263632A (en) | 2022-04-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111234960.0A Pending CN114263632A (en) | 2021-10-22 | 2021-10-22 | Rotor component of engine fan |
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| CN (1) | CN114263632A (en) |
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| US20190277192A1 (en) * | 2018-03-09 | 2019-09-12 | General Electric Company | Compressor rotor cooling apparatus |
| CN111456816A (en) * | 2020-04-09 | 2020-07-28 | 中国航发沈阳发动机研究所 | Stator blade anti-drop mounting structure |
| CN213598026U (en) * | 2020-11-02 | 2021-07-02 | 中国航发商用航空发动机有限责任公司 | Impeller machinery and aeroengine |
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2021
- 2021-10-22 CN CN202111234960.0A patent/CN114263632A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100166561A1 (en) * | 2008-12-30 | 2010-07-01 | General Electric Company | Turbine blade root configurations |
| CN102953764A (en) * | 2011-08-23 | 2013-03-06 | 通用电气公司 | Coupled blade platforms and methods of sealing |
| US20150047191A1 (en) * | 2013-08-19 | 2015-02-19 | Rolls-Royce Deutschland Ltd & Co Kg | Method for balancing and assembling a turbine rotor |
| CN205001254U (en) * | 2015-09-29 | 2016-01-27 | 中航商用航空发动机有限责任公司 | Rotor blade dish, compressor and aeroengine |
| CN107524477A (en) * | 2016-06-20 | 2017-12-29 | 中国航发商用航空发动机有限责任公司 | For eliminating the instrument and method of High Pressure Turbine Rotor blade joint gap |
| EP3290637A1 (en) * | 2016-08-31 | 2018-03-07 | United Technologies Corporation | Tandem rotor blades with cooling features |
| US20190277192A1 (en) * | 2018-03-09 | 2019-09-12 | General Electric Company | Compressor rotor cooling apparatus |
| CN109630204A (en) * | 2018-11-27 | 2019-04-16 | 中国航发沈阳发动机研究所 | A kind of rotor balancing clump weight fixed structure |
| CN111456816A (en) * | 2020-04-09 | 2020-07-28 | 中国航发沈阳发动机研究所 | Stator blade anti-drop mounting structure |
| CN213598026U (en) * | 2020-11-02 | 2021-07-02 | 中国航发商用航空发动机有限责任公司 | Impeller machinery and aeroengine |
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