CN110701102A - Engine fan rotor with fan rotor blade structure pole provided with same - Google Patents
Engine fan rotor with fan rotor blade structure pole provided with same Download PDFInfo
- Publication number
- CN110701102A CN110701102A CN201910935172.0A CN201910935172A CN110701102A CN 110701102 A CN110701102 A CN 110701102A CN 201910935172 A CN201910935172 A CN 201910935172A CN 110701102 A CN110701102 A CN 110701102A
- Authority
- CN
- China
- Prior art keywords
- fan rotor
- blade
- ring
- butt joint
- blade structure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
- F04D29/327—Rotors specially for elastic fluids for axial flow pumps for axial flow fans with non identical blades
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
- F04D29/386—Skewed blades
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/388—Blades characterised by construction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The application belongs to engine fan rotor structural design field, concretely relates to fan rotor blade structure, include: a reinforcement ring; the blade tip blades are distributed on the outer side of the reinforcing ring along the circumferential direction, and the root of each blade tip blade is connected with the outer wall of the reinforcing ring; the main runner blades are distributed on the inner side of the reinforcing ring along the circumferential direction, and the tip of each main runner blade is connected with the inner wall of the reinforcing ring. And, to an engine fan rotor comprising: a fan rotor disk; in the above fan rotor blade structure, the root of each main flow channel blade of the fan rotor blade structure is connected to the outer peripheral wall surface of the fan rotor disk.
Description
Technical Field
The application belongs to the field of structural design of engine fan rotors, and particularly relates to a fan rotor blade structure and an engine fan rotor with the same.
Background
The variable-cycle engine is mainly provided with two ducts, the engine fan inlet is provided with a single duct, the fan outlet is divided into an inner duct and an outer duct through an intermediate casing shunting ring, and on the basis, the self-adaptive variable-cycle engine is provided.
At present, only one layer of blades are arranged on the rotor blades of the engine, independent work on a third duct cannot be achieved, and the requirement of the self-adaptive variable-cycle engine cannot be met.
The present application is made in view of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide a fan rotor blade structure and an engine fan rotor having the same to overcome or alleviate at least one of the disadvantages of the prior art.
The technical scheme of the application is as follows:
one aspect provides a fan rotor blade structure comprising:
a reinforcement ring;
the blade tip blades are distributed on the outer side of the reinforcing ring along the circumferential direction, and the root of each blade tip blade is connected with the outer wall of the reinforcing ring;
the main runner blades are distributed on the inner side of the reinforcing ring along the circumferential direction, and the tip of each main runner blade is connected with the inner wall of the reinforcing ring.
According to at least one embodiment of the present application, a reinforcement ring includes:
the ring comprises a plurality of ring segments, a first butt joint edge and a second butt joint edge, wherein each ring segment is provided with the first butt joint edge and the second butt joint edge opposite to the first butt joint edge; the first butt edge of each ring segment is butted with the second butt edge of another ring segment, so that a reinforcing ring is formed.
According to at least one embodiment of the present application, the first butt edge and the second butt edge of each ring segment are serrated.
According to at least one embodiment of the present application, the first butt edge and its second butt edge of each ring segment are brazed with a wear resistant metal coating.
According to at least one embodiment of the application, the root of each tip blade is correspondingly connected with the outer wall of one ring segment;
the tip of each main runner blade is correspondingly connected with the inner wall of one ring segment.
According to at least one embodiment of the present application, each ring segment is integrally formed with a corresponding tip blade, primary flowpath blade.
According to at least one embodiment of the present application, each tip blade, each main runner blade has a pretwist angle.
Another aspect provides an engine fan rotor comprising:
a fan rotor disk;
any one of the above fan rotor blade structures, a root portion of each of the main flow path blades of the fan rotor blade structure is connected to a peripheral wall surface of the fan rotor disk.
According to at least one embodiment of the present application, the outer peripheral wall surface of the fan rotor disk has a plurality of circumferentially distributed mortises;
the root of each main runner blade is provided with a tenon which is correspondingly clamped into one mortise.
According to at least one embodiment of the application, the root of each main runner blade is provided with a collar and a bolt, locking a tenon on the root in a corresponding mortise.
According to at least one embodiment of the present application, the stiffening ring of the fan rotor blade structure has labyrinth teeth on both sides to seal with the fan stator on both sides thereof.
Drawings
FIG. 1 is a schematic structural diagram of a fan rotor of an engine provided in an embodiment of the present application;
FIG. 2 is a schematic view of the portion of FIG. 1 taken from the direction A;
FIG. 3 is a schematic partial structural view of a fan rotor of an engine provided in an embodiment of the present application;
FIG. 4 is a schematic view of a tenon being snapped into a mortise provided by an embodiment of the present application;
wherein:
1-a reinforcement ring; 2-tip blade; 3-a main runner vane; 4-a fan rotor disk; 5-a collar; 6-upper fan stator; 7-descending the fan stator.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Furthermore, it should be noted that, in the description of the present application, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.
The present application is described in further detail below with reference to fig. 1 to 4.
One aspect provides a fan rotor blade structure comprising:
a reinforcement ring 1;
the blade tip blades 2 are distributed on the outer side of the reinforcing ring 1 along the circumferential direction, and the root of each blade tip blade 2 is connected with the outer wall of the reinforcing ring 1;
a plurality of main runner blades 3, along the circumference distribution at the stiffening ring 1 inboard, the tip of every main runner blade 3 is connected with the inner wall of stiffening ring 1.
For the fan rotor blade structure provided by the above embodiment, those skilled in the art can understand that the main runner blade and the blade tip blade are respectively arranged on the inner side and the outer side of the reinforcing ring 1, and the fan rotor blade structure is of a layered blade structure, and can be installed on a rotor disk of an engine fan, and can independently do work on a third duct of the adaptive variable-cycle engine through the blade tip blade 2, so that the requirements of the adaptive variable-cycle engine are met, and the performance of the whole engine is improved.
In some alternative embodiments, the reinforcement ring 1 comprises:
the ring comprises a plurality of ring segments, a first butt joint edge and a second butt joint edge, wherein each ring segment is provided with the first butt joint edge and the second butt joint edge opposite to the first butt joint edge; the first butt edge of each ring segment is butted with the second butt edge of another ring segment, so that the reinforcing ring 1 is formed.
With respect to the fan rotor blade structure provided in the above embodiments, it will be understood by those skilled in the art that the reinforcing ring 1 is formed by a plurality of ring segments connected end to end, which facilitates assembly and assembly.
In some alternative embodiments, the first and second butt edges of each ring segment are serrated.
With respect to the fan rotor blade structure provided in the above embodiments, it can be understood by those skilled in the art that the first butt edge and the second butt edge of each ring segment are serrated, that is, the serration engagement between two adjacent ring segments in the reinforcement ring 1 has strong structural stability.
In some alternative embodiments, the first butt edge and its second butt edge of each ring segment are brazed with a wear resistant metal coating to avoid wear.
In some alternative embodiments, the root of each tip blade 2 is connected to the outer wall of a corresponding ring segment;
the tip of each main flow channel blade 3 is correspondingly connected with the inner wall of one ring segment.
In some alternative embodiments, each ring segment is integrally formed with the corresponding tip blade 2, primary flowpath blade 3.
To the fan rotor blade structure that above-mentioned embodiment provided, skilled person in the art can understand, it sets up every ring section and 2, the 3 integrated into one piece of sprue blade that correspond, can be convenient for the assembly between fan rotor blade structural component, can be when limited apex blade 2, sprue blade 3 damage, can convenient and fast's realization is to the independent change of this limited apex blade 2, sprue blade 3.
In some alternative embodiments, each tip blade 2, each main runner blade 3 has a pretwist angle.
With respect to the fan rotor blade structure provided in the above embodiments, it can be understood by those skilled in the art that each of the blade tip blades 2 and the main runner blade 3 has a pre-twisted angle, so that the first butt edge and the second butt edge of each ring segment of the stiffening ring 1 can be pre-twisted, and the stiffening ring 1 is formed as a rigid interlocking ring, so that the fan rotor blade structure has strong rigidity and good vibration resistance when being installed on an engine fan.
Another aspect provides an engine fan rotor comprising:
a fan rotor disk 4;
any one of the above-described fan rotor blade structures, a root portion of each of the main flow path blades 3 of which is connected to the outer peripheral wall surface of the fan rotor disk 4.
For the engine fan rotor provided in the above embodiment, as can be understood by those skilled in the art, the fan rotor blade structure and the fan rotor disk 4 constitute an engine fan rotor, and the engine fan is provided with the engine fan, and the engine fan can independently do work on the third duct of the adaptive variable cycle engine through the blade tip 2 of the fan rotor blade structure.
In some alternative embodiments, the peripheral wall surface of the fan rotor disk 4 has a plurality of circumferentially distributed mortises;
the root of each main runner blade 3 has a tenon, which correspondingly snaps into a mortise.
With regard to the engine fan rotor provided in the above embodiment, it can be understood by those skilled in the art that the assembly of the main runner blade 3 on the fan rotor disk 4 is realized through the form of tenon and mortise matching, and the structural stability is better.
With regard to the engine fan rotor provided in the above embodiment, it will be understood by those skilled in the art that the tenons at the root of each main runner blade 3 on the fan rotor blade structure may be correspondingly pushed into the mortises on the outer peripheral wall surface of the fan rotor disk 4 after the fan rotor blade structure is assembled.
In some alternative embodiments, the root of each main runner blade 3 is provided with a collar 5 and bolts locking the tenon on the root in the corresponding mortise to avoid relative axial movement.
In some alternative embodiments, the stiffening ring 1 of the fan rotor blade structure has labyrinth teeth on both sides to seal with the fan stators on both sides thereof.
For the engine fan rotor provided in the above embodiment, those skilled in the art can understand that the fan rotor blade structure may be disposed at any stage of the engine fan according to actual needs, independently do work on the third duct of the adaptive variable cycle engine through the blade tip blades 2, and dispose the labyrinth teeth on both sides of the stiffener ring 1 to achieve sealing with the fan stators on both sides of the engine fan rotor, that is, to achieve sealing with the fan stator 6 on the upper stage and the descending fan stator 7 of the engine fan rotor, so as to avoid flow leakage from the main duct to the third duct, which causes the third duct to be blocked, resulting in performance degradation of the adaptive variable cycle engine.
So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.
Claims (10)
1. A fan rotor blade structure, comprising:
a reinforcement ring (1);
the blade tip blades (2) are distributed on the outer side of the reinforcing ring (1) along the circumferential direction, and the root of each blade tip blade (2) is connected with the outer wall of the reinforcing ring (1);
a plurality of sprue vanes (3) distributed along the circumferential direction inside the reinforcing ring (1), and the tip of each sprue vane (3) is connected with the inner wall of the reinforcing ring (1).
2. The fan rotor blade structure according to claim 1,
the reinforcement ring (1) comprises:
the ring comprises a plurality of ring segments, a first butt joint edge and a second butt joint edge, wherein each ring segment is provided with the first butt joint edge and the second butt joint edge opposite to the first butt joint edge; the first butt edge of each ring segment is butted with the second butt edge of another ring segment, so that the reinforcing ring (1) is formed.
3. The fan rotor blade structure according to claim 2,
the first butt joint edge and the second butt joint edge of each ring segment are in a sawtooth shape.
4. The fan rotor blade structure according to claim 3,
and brazing the wear-resistant metal coating on the first butt joint edge and the second butt joint edge of each ring segment.
5. The fan rotor blade structure according to claim 3,
the root of each blade tip blade (2) is correspondingly connected with the outer wall of one ring segment;
the tip of each main runner blade (3) is correspondingly connected with the inner wall of one ring segment.
6. The fan rotor blade structure according to claim 5,
each ring segment is integrally formed with the corresponding blade tip blade (2) and the main runner blade (3).
7. The fan rotor blade structure according to claim 6,
each blade tip blade (2) and each main runner blade (3) have a pre-twist angle.
8. An engine fan rotor, comprising:
a fan rotor disk (4);
the fan rotor blade structure in accordance with any one of claims 1 to 5, a root portion of each main flow path blade (3) of the fan rotor blade structure being connected to a peripheral wall surface of the fan rotor disk (4).
9. The fan rotor according to claim 8,
the peripheral wall surface of the fan rotor disc (4) is provided with a plurality of mortises distributed along the circumferential direction;
the root of each main runner blade (3) is provided with a tenon which is correspondingly clamped into a mortise.
10. The fan rotor according to claim 9,
the root of each main runner blade (3) is provided with a clamping ring (5) and a bolt, and a tenon on the root is locked in a corresponding mortise.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910935172.0A CN110701102A (en) | 2019-09-29 | 2019-09-29 | Engine fan rotor with fan rotor blade structure pole provided with same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910935172.0A CN110701102A (en) | 2019-09-29 | 2019-09-29 | Engine fan rotor with fan rotor blade structure pole provided with same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110701102A true CN110701102A (en) | 2020-01-17 |
Family
ID=69196418
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910935172.0A Pending CN110701102A (en) | 2019-09-29 | 2019-09-29 | Engine fan rotor with fan rotor blade structure pole provided with same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110701102A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114294263A (en) * | 2021-10-20 | 2022-04-08 | 中国航发四川燃气涡轮研究院 | Fan blade disc structure and turbofan engine |
| CN114542510A (en) * | 2022-02-23 | 2022-05-27 | 中国航发沈阳发动机研究所 | Self-adaptive variable-cycle engine fan rotor structure |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5261227A (en) * | 1992-11-24 | 1993-11-16 | General Electric Company | Variable specific thrust turbofan engine |
| EP1895142A2 (en) * | 2006-07-31 | 2008-03-05 | General Electric Company | Flade fan with different inner and outer airfoil stagger angles at a shroud therebetween |
| DE102008023326A1 (en) * | 2008-05-13 | 2009-11-19 | Mtu Aero Engines Gmbh | Shroud for blades of a turbomachine and turbomachine |
| CN102877892A (en) * | 2012-10-23 | 2013-01-16 | 湖南航翔燃气轮机有限公司 | Turbine rotor blade and gas turbine with same |
| CN102926819A (en) * | 2012-10-23 | 2013-02-13 | 如皋透平叶片制造有限公司 | Anti-channeling dynamic integral shroud of turbine blade |
| CN104454026A (en) * | 2014-11-09 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Zigzag-shroud of aero-engine rotor vane |
| CN204941607U (en) * | 2015-09-07 | 2016-01-06 | 中国南方航空工业(集团)有限公司 | Turbine rotor |
| US20180010463A1 (en) * | 2016-07-06 | 2018-01-11 | General Electric Company | Turbine engine and method of assembling |
| CN109779783A (en) * | 2019-04-08 | 2019-05-21 | 沈阳建筑大学 | A kind of fanjet with the autonomous regulating power of bypass ratio |
| CN109973155A (en) * | 2019-04-18 | 2019-07-05 | 中国航发沈阳发动机研究所 | A kind of method and aero-engine for preventing the hat dislocation of turbine rotor blade sawtooth |
-
2019
- 2019-09-29 CN CN201910935172.0A patent/CN110701102A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5261227A (en) * | 1992-11-24 | 1993-11-16 | General Electric Company | Variable specific thrust turbofan engine |
| EP1895142A2 (en) * | 2006-07-31 | 2008-03-05 | General Electric Company | Flade fan with different inner and outer airfoil stagger angles at a shroud therebetween |
| DE102008023326A1 (en) * | 2008-05-13 | 2009-11-19 | Mtu Aero Engines Gmbh | Shroud for blades of a turbomachine and turbomachine |
| CN102877892A (en) * | 2012-10-23 | 2013-01-16 | 湖南航翔燃气轮机有限公司 | Turbine rotor blade and gas turbine with same |
| CN102926819A (en) * | 2012-10-23 | 2013-02-13 | 如皋透平叶片制造有限公司 | Anti-channeling dynamic integral shroud of turbine blade |
| CN104454026A (en) * | 2014-11-09 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Zigzag-shroud of aero-engine rotor vane |
| CN204941607U (en) * | 2015-09-07 | 2016-01-06 | 中国南方航空工业(集团)有限公司 | Turbine rotor |
| US20180010463A1 (en) * | 2016-07-06 | 2018-01-11 | General Electric Company | Turbine engine and method of assembling |
| CN109779783A (en) * | 2019-04-08 | 2019-05-21 | 沈阳建筑大学 | A kind of fanjet with the autonomous regulating power of bypass ratio |
| CN109973155A (en) * | 2019-04-18 | 2019-07-05 | 中国航发沈阳发动机研究所 | A kind of method and aero-engine for preventing the hat dislocation of turbine rotor blade sawtooth |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114294263A (en) * | 2021-10-20 | 2022-04-08 | 中国航发四川燃气涡轮研究院 | Fan blade disc structure and turbofan engine |
| CN114542510A (en) * | 2022-02-23 | 2022-05-27 | 中国航发沈阳发动机研究所 | Self-adaptive variable-cycle engine fan rotor structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2948641B1 (en) | Seal assembly in a gas turbine engine including grooves in a radially outwardly facing side of a platform and in a inwardly facing side of an inner shroud | |
| US6942460B2 (en) | Vane wheel for radial turbine | |
| US10584604B2 (en) | Group of blade rows | |
| US9068513B2 (en) | Seal assembly including grooves in an inner shroud in a gas turbine engine | |
| JP2010216474A (en) | Gas turbine having seal assembly with cover plate and seal | |
| EP2597263B1 (en) | Bucket assembly for turbine system | |
| KR20180054661A (en) | A high-strength turbomachine impeller, a turbomachine including the impeller, and a manufacturing method | |
| CN102392692A (en) | Apparatus and system for sealing a turbine rotor | |
| CN110701102A (en) | Engine fan rotor with fan rotor blade structure pole provided with same | |
| WO2016056463A1 (en) | Stator-vane structure and turbofan engine employing same | |
| JP2012002234A (en) | Axial flow turbine | |
| US10041368B2 (en) | Turbine assembly | |
| JP2012112379A (en) | Turbomachine nozzle segment having integrated diaphragm | |
| ES2883801T3 (en) | Vane, vane segment and structural component for a turbomachinery and turbomachinery | |
| US20150267547A1 (en) | Group of blade rows | |
| US10465555B2 (en) | Airfoil for axial flow machine | |
| US20140363283A1 (en) | Shroud arrangement for a fluid flow machine | |
| US20200232327A1 (en) | Controlled flow runners for turbines | |
| JP2003090279A (en) | Hydraulic rotating machine vane | |
| US9394797B2 (en) | Turbomachine nozzle having fluid conduit and related turbomachine | |
| US11408289B2 (en) | Moving blade of a turbo machine | |
| US10030521B2 (en) | Group of blade rows | |
| ES2887235T3 (en) | Gas Turbine Moving Blade | |
| US10648339B2 (en) | Contouring a blade/vane cascade stage | |
| EP2917495B1 (en) | A blade cascade for a turbomachine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200117 |