CN114714278B - Aeroengine low pressure turbine rotor blade balancing weight mounting fixture - Google Patents
Aeroengine low pressure turbine rotor blade balancing weight mounting fixture Download PDFInfo
- Publication number
- CN114714278B CN114714278B CN202210322922.9A CN202210322922A CN114714278B CN 114714278 B CN114714278 B CN 114714278B CN 202210322922 A CN202210322922 A CN 202210322922A CN 114714278 B CN114714278 B CN 114714278B
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- Prior art keywords
- bent
- clamping groove
- pressure turbine
- turbine rotor
- rotor blade
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- 238000005452 bending Methods 0.000 claims abstract description 57
- 238000009434 installation Methods 0.000 description 8
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
- B25B11/02—Assembly jigs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25J—MANIPULATORS; CHAMBERS PROVIDED WITH MANIPULATION DEVICES
- B25J1/00—Manipulators positioned in space by hand
- B25J1/04—Manipulators positioned in space by hand rigid, e.g. shelf-reachers
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Robotics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application relates to an aeroengine low pressure turbine rotor blade balancing weight mounting fixture, include: a connecting rod; a bending part chuck connected to one end of the connecting rod and provided with a bending part clamping groove; the bending part clamping groove can be clamped on the bending part of the balancing weight; the clamping head at the part to be bent is hinged with the clamping head at the part to be bent, and is provided with a clamping groove at the part to be bent; the clamping groove at the part to be bent can be clamped on the part to be bent of the balancing weight; the elastic sheet is connected between the clamping head at the bending part and the clamping head at the part to be bent, and the included angle between the clamping groove at the bending part and the clamping groove at the part to be bent is enlarged by virtue of elastic force; one end of the connecting rope is connected with the clamping head at the part to be bent, the other end of the connecting rope extends to the other end of the connecting rod, and the clamping head at the part to be bent can be pulled to overcome the elastic force of the elastic sheet to rotate, so that the included angle between the clamping groove at the part to be bent and the clamping groove at the part to be bent is reduced, the part to be bent is bent, and the balancing weight is mounted on the blade tip of the low-pressure turbine rotor blade.
Description
Technical Field
The application belongs to the technical field of installation design of low-pressure turbine rotor blade balancing weights of aero-engines, and particularly relates to an installation clamp for the low-pressure turbine rotor blade balancing weights of aero-engines.
Background
In order to balance the aeroengine rotor component, a balancing weight is arranged on the blade tip of the low-pressure turbine rotor blade, the balancing weight is provided with a bending part and a part to be bent, wherein the bending part is used for being clamped at the edge part of the blade tip of the low-pressure turbine rotor blade, the part to be bent is clamped at the edge part of the blade tip of the low-pressure turbine rotor blade after being bent, and the balancing weight is matched with the bending part, so that the balancing weight is reliably connected to the blade tip of the low-pressure turbine rotor blade.
The low-pressure turbine rotor blade of the aeroengine is positioned in the nozzle, when the balancing weight is installed on the blade tip of the aeroengine, the nozzle of the aeroengine is detached firstly to expose the low-pressure turbine rotor blade, the balancing weight is manually installed on the blade tip of the low-pressure turbine rotor blade, and the nozzle of the aeroengine is reinstalled after the installation is completed, so that the process is complicated, the installation is performed manually, and the efficiency is low.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present invention, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and the creativity of the present application in the case where no clear evidence indicates 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 aero-engine low pressure turbine rotor blade balancing weight mounting fixture that overcomes or mitigates at least one of the known technical drawbacks.
The technical scheme of the application is as follows:
an aircraft engine low pressure turbine rotor blade balancing weight mounting fixture, comprising:
a connecting rod;
a bending part chuck connected to one end of the connecting rod and provided with a bending part clamping groove; the bending part clamping groove can be clamped on the bending part of the balancing weight;
the clamping head at the part to be bent is hinged with the clamping head at the part to be bent, and is provided with a clamping groove at the part to be bent; the clamping groove at the part to be bent can be clamped on the part to be bent of the balancing weight;
the elastic sheet is connected between the clamping head at the bending part and the clamping head at the part to be bent, and the included angle between the clamping groove at the bending part and the clamping groove at the part to be bent is enlarged by virtue of elastic force;
one end of the connecting rope is connected with the clamping head at the part to be bent, the other end of the connecting rope extends to the other end of the connecting rod, the clamping head at the part to be bent can be pulled to overcome the elastic force of the elastic piece to rotate around the hinging part of the clamping head at the part to be bent, so that the included angle between the clamping groove at the part to be bent and the clamping groove at the part to be bent is reduced, and the balancing weight is arranged on the blade tip of the low-pressure turbine rotor blade.
According to at least one embodiment of the application, in the mounting fixture for the balancing weight of the low-pressure turbine rotor blade of the aeroengine, clamping grooves are formed between the clamping heads at the bending part and the clamping heads at the part to be bent;
the included angle between the clamping groove at the bending part and the clamping groove at the part to be bent is reduced, and when the part to be bent is bent, the clamping groove is clamped on the blade body of the low-pressure turbine rotor blade.
According to at least one embodiment of the application, in the mounting fixture for the balancing weight of the low-pressure turbine rotor blade of the aeroengine, a limiting hole is formed in a chuck at a position to be bent;
aeroengine low pressure turbine rotor blade balancing weight mounting fixture still includes:
the limiting pin is arranged in the limiting hole and connected to the clamping head at the bending part and is in clearance fit with the limiting hole so as to limit the range of an included angle between the clamping groove at the bending part and the clamping groove at the part to be bent.
According to at least one embodiment of the present application, in the aero-engine low-pressure turbine rotor blade balancing weight mounting fixture, the connecting rod is hollow;
the bending part clamp is provided with a through hole and a mounting groove; the through hole is communicated with the mounting groove;
aeroengine low pressure turbine rotor blade balancing weight mounting fixture still includes:
a pulley mounted in the mounting groove;
one end of the connecting rope, which is opposite to the chuck at the part to be bent, passes through the through hole, bypasses the pulley and extends out of the connecting rod.
According to at least one embodiment of the present application, in the above-mentioned installation fixture for a low-pressure turbine rotor blade balancing weight of an aeroengine, one end of the connecting rod, which faces away from the clamping head at a bending part, is bent, and the bending part is provided with a perforation;
the connecting rope is opposite to one end of the chuck at the part to be bent and extends out of the through hole.
According to at least one embodiment of the present application, in the above-mentioned aircraft engine low pressure turbine rotor blade balancing weight mounting fixture, further include
The handle is connected with one end of the connecting rope, which is opposite to the chuck at the position to be bent, and is hinged with one end of the connecting rod, which is opposite to the chuck at the position to be bent, and can pull the connecting rope when rotating around the hinged position of the connecting rod.
Drawings
FIG. 1 is a schematic illustration of an aircraft engine low pressure turbine rotor blade balancing weight mounting fixture provided by an embodiment of the present application;
FIG. 2 is a partial cross-sectional view of an aircraft engine low pressure turbine rotor blade weight mounting fixture provided by an embodiment of the present application;
FIG. 3 is a schematic illustration of an aircraft engine low pressure turbine rotor blade balancing weight mounting fixture in cooperation with a low pressure turbine rotor blade and balancing weights provided in an embodiment of the present application;
FIG. 4 is a schematic illustration of an aircraft engine low pressure turbine rotor blade balancing weight mounting fixture for mounting a balancing weight provided by an embodiment of the present application;
wherein:
1-a connecting rod; 2-clamping heads at the bending parts; 3-balancing weight; 4, clamping the part to be bent; 5-an elastic sheet; 6-connecting ropes; 7-low pressure turbine rotor blades; 8-limiting pins; 9-pulleys; 10-a handle; 11-spout.
For the purpose of better illustrating the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions, and furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the invention are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term and that is listed after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The present application is described in further detail below with reference to fig. 1-4.
An aircraft engine low pressure turbine rotor blade balancing weight mounting fixture, comprising:
a connecting rod 1;
a bending part clamping head 2 connected with one end of the connecting rod 1 and provided with a bending part clamping groove; the bending part clamping groove can be clamped on the bending part of the balancing weight 3;
the clamping head 4 at the part to be bent is hinged with the clamping head 2 at the part to be bent, and is provided with a clamping groove at the part to be bent; the clamping groove at the part to be bent can be clamped on the part to be bent of the balancing weight 3;
the elastic sheet 5 is connected between the clamping head 2 at the bending part and the clamping head 4 at the part to be bent, and the included angle between the clamping groove at the bending part and the clamping groove at the part to be bent is enlarged by virtue of elastic force;
one end of the connecting rope 6 is connected with the clamping head 4 at the part to be bent, the other end of the connecting rope extends to the other end of the connecting rod 1, the clamping head 4 at the part to be bent can be pulled to overcome the elastic force of the elastic piece 5 to rotate around the hinging part of the clamping head 2 at the part to be bent, the clamping grooves at the bending part and the included angles between the clamping grooves at the part to be bent are reduced, the part to be bent is bent, and the balancing weight 3 is mounted on the blade tip of the low-pressure turbine rotor blade 7.
The mounting fixture for the low-pressure turbine rotor blade balancing weight of the aero-engine disclosed by the embodiment can be used for mounting the low-pressure turbine rotor blade balancing weight of the aero-engine, and can be used for referring to the following steps:
the special tool passes through the jet 10 of the aeroengine, and the bending part of the balancing weight 3 is clamped to the edge part of the blade tip of the low-pressure turbine rotor blade 7;
one end of the connecting rod 1, which is connected with the bending part chuck 2, passes through the aeroengine nozzle 10, and the bending part clamping groove is clamped on the bending part of the balancing weight 3;
the connecting rope 6 is pulled to enable the chuck 4 at the part to be bent to rotate, the part to be bent is bent, and therefore the balancing weight 3 is mounted on the tip of the low-pressure turbine rotor blade 7.
For the aeroengine low pressure turbine rotor blade balancing weight mounting fixture disclosed by the embodiment, the skilled person can understand that the aeroengine low pressure turbine rotor blade balancing weight is mounted by the fixture, the connecting rod 1 can drive the bending part clamping head 2 and the clamping head 4 to be bent to penetrate through the aeroengine nozzle 10, the installation of the balancing weight 3 at the tip part of the low pressure turbine rotor blade 7 is realized by pulling the external connecting rope 6, the mounting of the balancing weight 3 at the tip part of the low pressure turbine rotor blade 7 is convenient and quick, the disassembly and assembly of the aeroengine nozzle 10 are not needed, the efficiency is higher, after the mounting of the balancing weight 3 is completed, the bending part clamping head 2 and the clamping head 4 to be bent can be separated under the action of the elastic force of the elastic piece 5, and the balancing weight 3 is convenient to take down.
In some alternative embodiments, in the above-mentioned installation fixture for balancing weight of low-pressure turbine rotor blade of aero-engine, clamping grooves are formed between the clamping heads 2 and the clamping heads 4 at the positions to be bent;
the included angle between the clamping groove at the bending part and the clamping groove at the part to be bent is reduced, and when the part to be bent is bent, the clamping groove is clamped on the blade body of the low-pressure turbine rotor blade 7, so that the positioning of the balancing weight of the low-pressure turbine rotor blade of the aero-engine during installation is facilitated.
In some alternative embodiments, in the above-mentioned mounting fixture for the low-pressure turbine rotor blade balancing weight of the aero-engine, the clamping head 4 at the position to be bent is provided with a limiting hole;
aeroengine low pressure turbine rotor blade balancing weight mounting fixture still includes:
the limiting pin 8 is arranged in the limiting hole and connected to the bending part clamping head 2 in clearance fit with the limiting hole so as to limit the range of included angles between the bending part clamping groove and the clamping groove to be bent, avoid too small or too large included angles between the bending part clamping groove and the clamping groove to be bent, facilitate operation and avoid damage to the low-pressure turbine rotor blade 7 and the balancing weight 3 of the low-pressure turbine rotor blade.
In some alternative embodiments, in the aero-engine low pressure turbine rotor blade balancing weight mounting fixture described above, the connecting rod 1 is hollow;
the bending part clamping head 2 is provided with a through hole and a mounting groove; the through hole is communicated with the mounting groove;
aeroengine low pressure turbine rotor blade balancing weight mounting fixture still includes:
a pulley 9 mounted in the mounting groove;
one end of the connecting rope 6, which is opposite to the chuck 4 at the part to be bent, passes through the through hole, bypasses the pulley 9 and extends out of the connecting rod 1.
For the aeroengine low pressure turbine rotor blade balancing weight mounting fixture disclosed in the above embodiment, it can be understood by those skilled in the art that the pulley 9 is designed to realize the steering of the connecting rope 6, so that the connecting rope 6 extends out of the connecting rod 1, the position of the connecting rope 6 can be effectively restrained, the force application direction of the connecting rope 6 is ensured, and the operation is convenient.
In some alternative embodiments, in the above-mentioned mounting fixture for the low-pressure turbine rotor blade balancing weight of the aeroengine, one end of the connecting rod 1, which faces away from the clamping head 2 at the bending position, is bent, and the bending position is provided with a perforation;
the connecting rope 6 is extended out from the through hole at one end of the chuck 4 at the position to be bent, and when the balancing weight of the low-pressure turbine rotor blade of the aeroengine is installed, one bent end of the connecting rod 1 can be used as a support to drive the connecting rope 6.
In some alternative embodiments, the aircraft engine low pressure turbine rotor blade weight block mounting fixture further comprises
The handle 10 is connected with one end of the connecting rope 6, which is back to the chuck 4 at the position to be bent, and hinged with one end of the connecting rod 1, which is back to the chuck 2 at the bending position, and can drive the connecting rope 6 when rotating around the hinged position with the connecting rod 1, so that the operation is convenient.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.
Claims (4)
1. An aircraft engine low pressure turbine rotor blade balancing weight mounting fixture, comprising:
a connecting rod (1);
a bending part clamping head (2) connected to one end of the connecting rod (1) and provided with a bending part clamping groove; the bending part clamping groove can be clamped on the bending part of the balancing weight (3);
a clamping head (4) at the part to be bent is hinged with the clamping head (2) at the part to be bent, and a clamping groove at the part to be bent is formed in the clamping head; the clamping groove at the part to be bent can be clamped on the part to be bent of the balancing weight (3);
the elastic sheet (5) is connected between the bending part clamping head (2) and the part clamping head (4) to be bent, and the included angle between the clamping groove at the bending part and the clamping groove at the part to be bent is enlarged by means of elastic force;
one end of the connecting rope (6) is connected with the clamping head (4) at the part to be bent, the other end of the connecting rope extends to the other end of the connecting rod (1) and can drive the clamping head (4) at the part to be bent to overcome the elastic force of the elastic piece (5) to rotate around the hinging part of the clamping head (2) at the part to be bent, so that the included angle between the clamping groove at the part to be bent and the clamping groove at the part to be bent is reduced, and the balancing weight (3) is arranged on the blade tip of the low-pressure turbine rotor blade (7);
a clamping groove is formed between the bending part clamping head (2) and the part clamping head (4) to be bent;
the included angle between the clamping groove at the bending part and the clamping groove at the part to be bent is reduced, and when the part to be bent is bent, the clamping groove is clamped on the blade body of the low-pressure turbine rotor blade (7);
a limiting hole is formed in the chuck (4) at the part to be bent;
the aero-engine low-pressure turbine rotor blade balancing weight mounting fixture further comprises:
and the limiting pin (8) is arranged in the limiting hole and connected to the bending part clamping head (2) in clearance fit with the limiting hole so as to limit the range of an included angle between the bending part clamping groove and the clamping groove of the part to be bent.
2. The aircraft engine low pressure turbine rotor blade weight mounting fixture of claim 1,
the connecting rod (1) is hollow;
the bending part clamping head (2) is provided with a through hole and a mounting groove; the through hole is communicated with the mounting groove;
the aero-engine low-pressure turbine rotor blade balancing weight mounting fixture further comprises:
a pulley (9) mounted in the mounting groove;
one end of the connecting rope (6) back to the chuck (4) at the part to be bent passes through the through hole, bypasses the pulley (9) and extends out of the connecting rod (1).
3. The aircraft engine low pressure turbine rotor blade weight mounting fixture of claim 2,
one end of the connecting rod (1) back to the clamping head (2) at the bending part is bent, and the bending part is provided with a perforation;
the connecting rope (6) is opposite to one end of the chuck (4) at the part to be bent, and extends out of the through hole.
4. The aircraft engine low pressure turbine rotor blade weight mounting fixture of claim 3,
and also comprises
The handle (10) is connected with one end of the connecting rope (6) back to the chuck (4) at the position to be bent, is hinged to one end of the connecting rod (1) back to the chuck (2) at the position to be bent, and can drive the connecting rope (6) when rotating around the hinged position of the connecting rod (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210322922.9A CN114714278B (en) | 2022-03-29 | 2022-03-29 | Aeroengine low pressure turbine rotor blade balancing weight mounting fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210322922.9A CN114714278B (en) | 2022-03-29 | 2022-03-29 | Aeroengine low pressure turbine rotor blade balancing weight mounting fixture |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114714278A CN114714278A (en) | 2022-07-08 |
| CN114714278B true CN114714278B (en) | 2024-01-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210322922.9A Active CN114714278B (en) | 2022-03-29 | 2022-03-29 | Aeroengine low pressure turbine rotor blade balancing weight mounting fixture |
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| Country | Link |
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| CN (1) | CN114714278B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115203765B (en) * | 2022-07-29 | 2023-07-07 | 中国航发沈阳发动机研究所 | Design method of balancing weight for low-cycle fatigue test of aero-engine rotor |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1993019880A1 (en) * | 1992-04-04 | 1993-10-14 | GÖHRIG, Gerhard | Bolt or wire-mesh cutter |
| CN105662513A (en) * | 2015-12-31 | 2016-06-15 | 刘鸿箫 | Vascular occlusion forceps easy to detach and clean and capable of being freely bent |
| CN205415367U (en) * | 2016-03-09 | 2016-08-03 | 李明德 | Long locking pliers of double -rocker rhombus pincers mouth |
| CN206193054U (en) * | 2016-11-29 | 2017-05-24 | 贵州电网有限责任公司兴义供电局 | Multi -functional heavy current high altitude jointing clamp |
| CN215942797U (en) * | 2021-05-18 | 2022-03-04 | 中国航发商用航空发动机有限责任公司 | Mounting pliers for mounting balance snap spring |
-
2022
- 2022-03-29 CN CN202210322922.9A patent/CN114714278B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1993019880A1 (en) * | 1992-04-04 | 1993-10-14 | GÖHRIG, Gerhard | Bolt or wire-mesh cutter |
| CN105662513A (en) * | 2015-12-31 | 2016-06-15 | 刘鸿箫 | Vascular occlusion forceps easy to detach and clean and capable of being freely bent |
| CN205415367U (en) * | 2016-03-09 | 2016-08-03 | 李明德 | Long locking pliers of double -rocker rhombus pincers mouth |
| CN206193054U (en) * | 2016-11-29 | 2017-05-24 | 贵州电网有限责任公司兴义供电局 | Multi -functional heavy current high altitude jointing clamp |
| CN215942797U (en) * | 2021-05-18 | 2022-03-04 | 中国航发商用航空发动机有限责任公司 | Mounting pliers for mounting balance snap spring |
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| Publication number | Publication date |
|---|---|
| CN114714278A (en) | 2022-07-08 |
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