CN109488390B - Rotor blade connecting assembly and turbine performance test assembly - Google Patents
Rotor blade connecting assembly and turbine performance test assembly Download PDFInfo
- Publication number
- CN109488390B CN109488390B CN201811549250.5A CN201811549250A CN109488390B CN 109488390 B CN109488390 B CN 109488390B CN 201811549250 A CN201811549250 A CN 201811549250A CN 109488390 B CN109488390 B CN 109488390B
- Authority
- CN
- China
- Prior art keywords
- rotor blade
- assembly
- annular baffle
- pin shaft
- conical pin
- 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.)
- Active
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application provides a rotor blade coupling assembling and turbine performance test subassembly. The rotor blade connection assembly includes: the blade mounting structure comprises a blade mounting hole, a plurality of double-lug structures and a plurality of conical pin shafts, wherein one conical pin shaft is used for being connected with the double-lug structures through one blade mounting hole; the annular baffle is connected with the turbine disc and arranged on the windward side of the airflow of the turbine disc, and one surface of the annular baffle is opposite to the end surface of one end of the conical pin shaft; a plurality of axial holding rings, the axial holding ring sets up annular baffle with between the taper pin axle, and an axial holding ring corresponds with a taper pin axle, the axial holding ring is installed annular baffle is last, the axial holding ring has and supports to lean on the portion, support to lean on the portion with the one end of taper pin axle with the terminal surface contact that the baffle is relative.
Description
Technical Field
The application belongs to the technical field of turbine performance tests, and particularly relates to a rotor blade connecting assembly and a turbine performance test assembly.
Background
The rotor blade connecting structure is a common structure on a turbine performance test piece and plays a role in positioning and connecting the rotor blades. The structure design and the processing of the simulated turbine performance test piece have certain requirements on economy and machinability on the basis of meeting the functionality. The common connecting structure of the turbine performance test piece rotor blade and the turbine disc comprises tongue-and-groove connection, a blisk, conventional pin lug connection and the like. Tongue and groove connection structures are common on turbine components of aircraft engines as a whole; the blisk structure is such that the rotor blades and the turbine disk are of a unitary structure.
In the simulation turbine performance test piece with lower working temperature and pressure, the tongue-and-groove connection and the blisk structure have corresponding defects, the processing difficulty is higher, the processing period is long, the economy is poorer, and the rapid test verification on the turbine performance is unfavorable. The conventional pin lug connection structure has the defect that the radial positioning between the rotor blade and the turbine disc is not accurate enough due to the gap between the pin and the pin hole. At present, a rotor blade connecting structure which meets the working requirements of a simulation turbine performance test piece, is simple and reliable in structure, accurate in positioning, convenient to machine and good in economical efficiency is lacked.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide a rotor blade connection assembly to address at least one problem with the prior art.
The technical scheme of the application is as follows:
a rotor blade attachment assembly for attaching a plurality of rotor blades having blade mounting holes to a turbine disk having a binaural configuration, the turbine disk having an airflow upwind side; characterized in that the rotor blade connection assembly comprises:
the blade mounting structure comprises a blade mounting hole, a plurality of double-lug structures and a plurality of conical pin shafts, wherein one conical pin shaft is used for being connected with the double-lug structures through one blade mounting hole;
the annular baffle is connected with the turbine disc and arranged on the windward side of the airflow of the turbine disc, and one surface of the annular baffle is opposite to the end surface of one end of the conical pin shaft;
a plurality of axial holding rings, the axial holding ring sets up the baffle with between the taper pin axle, and an axial holding ring corresponds with a taper pin axle, the axial holding ring is installed on the ring baffle, the holding ring has and supports to lean on the portion, support to lean on the portion with the one end of taper pin axle with the terminal surface contact that the baffle is relative.
Optionally, the radius of the tapered pin shaft is decreased from one end to the other end along the airflow direction.
Optionally, the axial positioning ring comprises:
a positioning ring body, the positioning ring body;
the elastic assembly is installed on the positioning ring body, and the abutting portion is arranged on the elastic assembly.
Optionally, the retaining ring body is welded to the annular baffle.
Optionally, an annular baffle mounting hole is formed in the double-lug structure;
the annular baffle is connected with the annular baffle mounting hole through a connecting piece.
Optionally, the resilient member is a spring plate.
Optionally, the spring plate is integrally formed with the retaining ring body.
Optionally, the number of the spring pieces is multiple.
The application also provides a turbine performance test assembly, turbine performance test assembly includes a plurality of rotor blades, turbine disc and as above rotor blade coupling assembling.
The application has at least the following beneficial technical effects:
the rotor blade connecting assembly is simple in structure, accurate in positioning, capable of meeting functional requirements, simple in process, low in machining cost, easy to assemble and low in economic cost.
Drawings
FIG. 1 is a schematic structural view of a rotor blade attachment assembly in an embodiment of the present application.
FIG. 2 is an enlarged partial view of the rotor blade attachment assembly of FIG. 1.
FIG. 3 is a schematic illustration of a tapered pin in the rotor blade attachment assembly shown in FIG. 1.
FIG. 4 is a schematic view of an axial locating ring in the rotor blade attachment assembly shown in FIG. 1.
FIG. 5 is a schematic illustration of a ring damper in the rotor blade attachment assembly shown in FIG. 1.
Reference numerals
1-a conical pin shaft; 2-axial positioning ring; 3-an annular baffle; 4-a connector; 5-rotor blades; 6-a turbine disk; 7-spring leaf.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. 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 are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The rotor blade attachment assembly shown in fig. 1 to 5 is used for attaching a plurality of rotor blades 5 to a turbine disk 6, the rotor blades 5 having blade mounting holes, the turbine disk 6 having a binaural structure, the turbine disk having one air flow windward side; rotor blade coupling assembling includes a plurality of taper pin axles 1, ring baffle 3 and a plurality of axial positioning ring 2.
Referring to fig. 1, a tapered pin 1 is used to connect with a double-lug structure through a blade mounting hole; a tapered pin corresponds to a rotor blade for mounting a rotor blade in a binaural configuration.
The annular baffle 3 is connected with the turbine disc 6 and arranged on the windward side of the airflow of the turbine disc 6, and one surface of the annular baffle 3 is opposite to the end surface of one end of the conical pin shaft 1;
Referring to fig. 3, in the present embodiment, the radius of the tapered pin is decreased from one end to the other end along the airflow direction.
Referring to fig. 4, in the present embodiment, the axial positioning ring includes a positioning ring body and an elastic component, and the positioning ring body is connected to the annular baffle; the elastic component is arranged on the positioning ring body, and the elastic component is provided with a leaning part.
In this embodiment, the retaining ring body is welded to the annular baffle.
In the embodiment, the double-lug structure is provided with an annular baffle mounting hole; the annular baffle is connected with the annular baffle mounting hole through a connecting piece.
In this embodiment, the elastic member is a spring plate 7.
In this embodiment, the spring plate 7 is integrally formed with the retaining ring body.
In this embodiment, the number of the spring pieces is plural.
The application also provides a turbine performance test assembly, turbine performance test assembly includes a plurality of rotor blades, turbine disc and as above rotor blade coupling assembling.
Referring to fig. 1-5, in the present embodiment, a turbine performance testing assembly includes:
a turbine disk 6 connected with the rotor blades;
the tapered pin shaft 1 is used for connecting the rotor blade and the turbine disc, and the radius of the tapered pin shaft along the airflow direction is from large to small;
the annular baffle 3 is arranged on the windward side of the airflow, and is fixed with the turbine disc 6 through a connecting piece 4 and used for axially positioning the conical pin shaft;
the axial positioning ring 2 is arranged between the annular baffle and the conical pin shaft, and is provided with an elastic sheet extending from the annular baffle to the conical pin shaft, and the elastic sheet is abutted against the front end face of the conical pin shaft and used for preventing the conical pin shaft from loosening in the axial direction.
The axial positioning ring 2 is formed by sheet metal processing, rib plates are processed at the inner diameter and the outer diameter of the annular thin plate to prevent deformation, the spring pieces with the same number of pins are processed in the circumferential direction and abut against the front end face of the conical pin shaft and are in one-to-one correspondence with the pin shaft, the front baffle plate 3 and the axial positioning ring 2 are welded to form a welding assembly, and the welding assembly is connected with the turbine disc 6 through a connecting piece 4 and is centered through a spigot.
The design has the advantages of simple structure, accurate positioning, functional requirement satisfaction, simple process, low processing cost, easy assembly and lower economic cost.
Parts such as a conical pin shaft, an axial positioning ring and a baffle plate in the rotor blade connecting assembly can be machined, a special tool is not needed, the process is simple, the cost is low, and the machining period is short; the conical pin shaft of the rotor blade connecting assembly is inserted into the conical hole of the connected piece, so that the connection is tight, the positioning is accurate, and the operation is reliable; according to the rotor blade connecting assembly, the conical pin shaft is inserted into the connecting hole, the baffle plate and the axial positioning ring welding assembly are connected with the turbine disc through the bolts, the assembly is simple, and the economy is good; the rotor blade connecting assembly is not only suitable for a simulation turbine performance test piece, but also can be applied to other mechanical connecting structures with low requirements on working temperature and pressure.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. A rotor blade connection assembly for connecting a plurality of rotor blades (5) to a turbine disc (6), the rotor blades (5) having blade mounting holes, the turbine disc (6) having a binaural configuration, the turbine disc having an airflow upwind side; characterized in that the rotor blade connection assembly comprises:
the conical pin shafts (1), one conical pin shaft (1) is used for being connected with the double-lug structure through one blade mounting hole;
the annular baffle (3) is connected with the turbine disc (6) and arranged on the windward side of the airflow of the turbine disc (6), and one surface of the annular baffle (3) is opposite to the end surface of one end of the conical pin shaft (1);
the axial positioning rings (2) are arranged between the annular baffle (3) and the conical pin shaft (1), one axial positioning ring (2) corresponds to one conical pin shaft (1), the axial positioning rings (2) are installed on the annular baffle (3), the axial positioning rings (2) are provided with abutting parts, and the abutting parts are in contact with the end face, opposite to the baffle, of one end of the conical pin shaft;
the radius of the conical pin shaft is from large to small from one end to the other end along the airflow direction.
2. The rotor blade attachment assembly of claim 1 wherein said axial positioning ring comprises:
the positioning ring body is connected with the annular baffle;
the elastic assembly is installed on the positioning ring body, and the abutting portion is arranged on the elastic assembly.
3. The rotor blade attachment assembly of claim 2 wherein said retaining ring body is welded to said annular barrier.
4. The rotor blade attachment assembly of claim 1 wherein said binaural structure is provided with an annular baffle mounting hole;
the annular baffle is connected with the annular baffle mounting hole through a connecting piece.
5. Rotor blade connecting assembly according to claim 2, wherein the resilient assembly is a spring plate (7).
6. Rotor blade connection assembly according to claim 5, wherein the leaf spring (7) is integrally formed with the retaining ring body.
7. The rotor blade attachment assembly of claim 6 wherein said spring plate is plural in number.
8. A turbine performance testing assembly comprising a plurality of rotor blades, a turbine disc and a rotor blade connection assembly according to any one of claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811549250.5A CN109488390B (en) | 2018-12-18 | 2018-12-18 | Rotor blade connecting assembly and turbine performance test assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811549250.5A CN109488390B (en) | 2018-12-18 | 2018-12-18 | Rotor blade connecting assembly and turbine performance test assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109488390A CN109488390A (en) | 2019-03-19 |
| CN109488390B true CN109488390B (en) | 2021-10-01 |
Family
ID=65710833
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811549250.5A Active CN109488390B (en) | 2018-12-18 | 2018-12-18 | Rotor blade connecting assembly and turbine performance test assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109488390B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110985134B (en) * | 2019-12-13 | 2022-06-21 | 西安鑫垚陶瓷复合材料有限公司 | Aeroengine ceramic matrix composite fixed guider blade structure and forming method thereof |
| JP7191881B2 (en) * | 2020-02-10 | 2022-12-19 | 三菱重工業株式会社 | Turbine wheel and fixing method of wire holding pin in turbine wheel |
| CN114718658B (en) * | 2021-01-05 | 2024-08-09 | 中国航发商用航空发动机有限责任公司 | Tool and method for controlling width of baffle ring mounting groove |
| CN114856719B (en) * | 2022-04-18 | 2024-08-02 | 中国航发沈阳发动机研究所 | Universal air system, structure and control method for turbine rotor test |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB868903A (en) * | 1959-10-13 | 1961-05-25 | Westinghouse Electric Corp | Improvements in or relating to bladed rotor structures for turbines and compressors |
| JPS52118106A (en) * | 1976-03-31 | 1977-10-04 | Agency Of Ind Science & Technol | Vane root part fixing device for turbine movable vane fitted with shro uds |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2844562B1 (en) * | 2002-09-18 | 2004-10-29 | Snecma Moteurs | CONTROL OF THE AXIAL POSITION OF A BLOWER ROTOR BLADE |
| FR2940350B1 (en) * | 2008-12-23 | 2011-03-18 | Snecma | MOBILE WHEEL OF TURBOMACHINE A AUBES COMPOSITE MATERIAL HAVING A SPRING RING. |
| US10864585B2 (en) * | 2017-03-13 | 2020-12-15 | General Electric Company | Machining system for turbomachine dovetail |
-
2018
- 2018-12-18 CN CN201811549250.5A patent/CN109488390B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB868903A (en) * | 1959-10-13 | 1961-05-25 | Westinghouse Electric Corp | Improvements in or relating to bladed rotor structures for turbines and compressors |
| JPS52118106A (en) * | 1976-03-31 | 1977-10-04 | Agency Of Ind Science & Technol | Vane root part fixing device for turbine movable vane fitted with shro uds |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109488390A (en) | 2019-03-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109488390B (en) | Rotor blade connecting assembly and turbine performance test assembly | |
| JP2003501581A (en) | Concentric rings | |
| CN110529214B (en) | Rocker arm axial limiting structure | |
| CN207961235U (en) | A kind of curved spring baffle ring | |
| CN108317154A (en) | A kind of curved spring baffle ring and its assembly method | |
| US7387301B2 (en) | Brush seal for sealing a gap between a rotor and a stator | |
| CN210344125U (en) | Disc spring for disc spring assembly and disc spring assembly | |
| CN208763696U (en) | A kind of constructional element with spring of Gas Turbine first order nozzle | |
| CN220699417U (en) | Damper ear plate connecting device | |
| CN220488043U (en) | Self-locking connecting device | |
| CN207332952U (en) | A kind of blade and aero-engine | |
| CN114673564B (en) | Fingertip sealing device | |
| CN210919393U (en) | Compressor shell with novel supporting leg assembly and compressor | |
| CN113566666B (en) | Low-pressure turbine rotation and stator axial distance measuring method | |
| CN214153249U (en) | Contact and connector | |
| CN213511681U (en) | Elastic retainer ring for cylindrical roller bearing | |
| CN207622228U (en) | Mounting structure and air conditioner of fan blade | |
| CN219842138U (en) | Manifold assembly target practice test tool | |
| CN209919743U (en) | Automobile ball cage positioning fixture | |
| CN216504626U (en) | Bearing positioning mechanism | |
| CN214325073U (en) | Self-positioning bushing and pedal arm assembly for brake pedal | |
| CN221075012U (en) | Bearing pedestal, bearing pedestal assembly thereof and air conditioner | |
| CN216717092U (en) | Shell-tube heat exchanger | |
| CN219535829U (en) | Motor shaft grounding assembly | |
| CN220732462U (en) | Novel structure of motor rotor |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |