CN110578557A - Turbine blade locking device and assembling method thereof - Google Patents
Turbine blade locking device and assembling method thereof Download PDFInfo
- Publication number
- CN110578557A CN110578557A CN201911040476.7A CN201911040476A CN110578557A CN 110578557 A CN110578557 A CN 110578557A CN 201911040476 A CN201911040476 A CN 201911040476A CN 110578557 A CN110578557 A CN 110578557A
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- Prior art keywords
- locking
- short
- long
- locking plate
- blade
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Classifications
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- 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
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a turbine blade locking device and an assembling method thereof, relating to the technical field of engines. According to the invention, the short locking plate is repaired and matched with the long locking plate for use, so that the blade is locked on the turbine disc to finally achieve the effect of locking the blade, and meanwhile, the wind shielding effect is achieved, and the gas leakage is reduced. Compared with the locking plate and the wind shield structure in the prior scheme, the invention is convenient to assemble and reduces the quality by 50 percent.
Description
Technical Field
The invention relates to the technical field of engines, in particular to a turbine blade locking device and an assembling method thereof.
Background
The high-pressure turbine of certain type engine, blade and turbine disc adopt the connection structure of tenon tooth and tongue-and-groove, in order to satisfy the intensity demand after the modification, turbine disc tongue-and-groove bottom adopts great transition space, and the locking plate in the original scheme adds the structural design of keeping off the wind piece and no longer is suitable for, and it is spacing to carry out the axial to the blade for this reason need design new locking plate structure, will play the effect of keeping off the wind simultaneously, reduces turbine gas leakage loss.
Disclosure of Invention
Technical problem to be solved
The technical problem to be solved by the invention is as follows: how to realize a locking device and an assembly method thereof, the axial limiting is carried out on a high-pressure turbine blade of an engine, and meanwhile, the wind shielding effect is realized, and the gas leakage loss of the turbine is reduced.
(II) technical scheme
In order to solve the technical problem, the invention provides a turbine blade locking device which is used for axially limiting a blade of a high-pressure turbine so as to lock the blade on a turbine disc and simultaneously has the function of a wind shield.
Preferably, the turbine blade locking device comprises a full circle locking piece arranged between the blade flange plate hanging lug and the turbine disc hanging lug; gaps among the locking plates are positioned in the middle of the tenon end faces of the blades, if the number of the blades is 47, the circumferential angle of each blade is 7.66 degrees, the whole circle of locking plates consists of 4 long locking plates and 1 short locking plate which are connected end to end, each long locking plate covers 11 blades, 4 long locking plates continuously cover 44 blades, and the short locking plates cover the rest 3 blades; the circumferential angle of the long locking plate is designed to be 84.3 degrees; the circumferential angle of the short locking tab is set to 24 °.
Preferably, the projection of the long locking piece is in a fan-shaped ring shape, two bending positions exist, an arc notch is formed in one end of the middle diameter position of the long locking piece, and the arc notch is located at the tenon end face of the blade.
Preferably, the short locking plate has two bending positions, the short locking plate has an intermediate forming state and a delivery state, the middle part of the two bending positions is bent in the intermediate forming state, and the bending angle of the two bending positions is larger than that of the two bending positions of the long locking plate in the delivery state.
The invention also provides an assembly method of the device, and 4 long locking plates and 1 short locking plate are sequentially installed during installation; in the process of assembling the long locking plate, the bent edge faces outwards, the arc notch is pushed to enable the 4 long locking plates to be in butt joint and tightly pushed, and meanwhile, the edge of the long locking plate is located in the middle of the tenon end face of the blade; when assembling short locking plate, at first repair short locking plate, guarantee that the gap width between short locking plate and the first long locking plate is at the certain limit, during the installation, middle bellied one side is outwards placed between blade flange hangers and turbine disc hangers, then strikes the flat with the bellied position of short locking plate with soft hammer.
Preferably, during assembly, the convex part of the short locking plate is knocked flat by a soft hammer.
Preferably, the short locking plate is repaired, and the width of the gap between the short locking plate and the first long locking plate is ensured to be 0.4 mm.
The invention also provides application of the device in a high-pressure turbine with a chamfer transition space at the bottom of the mortise of the turbine disc.
(III) advantageous effects
according to the invention, the short locking plate is repaired and matched with the long locking plate for use, so that the blade is locked on the turbine disc to finally achieve the effect of locking the blade, and meanwhile, the wind shielding effect is achieved, and the gas leakage is reduced. Compared with the locking plate and the wind shield structure in the prior scheme, the invention is convenient to assemble and reduces the quality by 50 percent.
Drawings
FIG. 1 is a schematic view of the assembly of a locking piece in the device designed according to the present invention;
FIG. 2 is a model view of a long locking piece of the present invention;
FIG. 3 is a model diagram of a short lock plate delivery state;
FIG. 4 is a model diagram of a short locking plate in a middle forming state;
FIG. 5 is a schematic view of the long blade assembly;
FIG. 6 is a schematic view of the short lock tab assembly;
Fig. 7 is a diagram showing the assembly effect of all locking plates, wherein a is an air inlet side view, b is an air outlet side view, and c is a drawing direction view (air inlet side) of the tenon tooth.
Detailed Description
In order to make the objects, contents, and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention will be made in conjunction with the accompanying drawings and examples.
The invention provides a turbine blade locking device which comprises a plurality of locking plates, wherein the locking plates are used for axially limiting blades of a high-pressure turbine so as to lock the blades on a turbine disc, and simultaneously, the locking plates play a role of wind shielding plates and reduce the air leakage loss of the turbine.
specifically, as shown in fig. 1, the turbine blade locking device is a full-circle locking plate arranged between a blade flange plate hanging lug and a turbine disc hanging lug, and can ensure axial limiting of a blade under the action of a blade installation angle and the elastic force of the locking plate, and simultaneously prevent air flow leakage at the bottom of a mortise of the turbine disc. In order to ensure that the splicing part of the locking plates can be locked with the blades, the gap between the locking plates is required to be positioned in the middle of the tenon end face of the blade, and therefore the value of the circumferential angle of the locking plates is directly related to the number of the blades. In the invention, the number of the blades is 47, and the circumferential angle of each blade is 360/47-7.66 degrees. In order to facilitate assembly, a scheme of 4 long locking pieces and 1 short locking piece is selected, each long locking piece can cover 11 blades, so that the 4 long locking pieces continuously cover 44 blades, and the short locking piece can cover the rest 3 blades; accordingly, the circumferential angle of the long locking piece is designed to be 84.3 degrees as 11 multiplied by 7.66 degrees; since the short locking piece needs to be manufactured with a certain margin in order to ensure the fitting, the circumferential angle is set to 24 ° (greater than 3 × 7.66 ° -22.98 °).
the structure of the long locking plate is shown in fig. 2, wherein a is a main view, b is a left view, the projection view of the long locking plate is in a fan-shaped ring shape, two bending positions exist, the long locking plate is guaranteed to generate elastic force by controlling the angle, an arc notch is formed in the left end of the middle diameter position of the long locking plate, the arc notch is located at the tenon end face of the blade, and the locking plate can be pushed to rotate circumferentially to be tightly pushed during assembly.
The structure of the short locking piece is shown in fig. 3 and 4, wherein a is a front view, b is a left view, and two bending positions exist. In order to facilitate the assembly, short locking plate has middle shaping state and delivery state, bend in the middle of two places of bending under middle shaping state and be convenient for place and adjust the repairment volume, allow to pass through to repair short locking plate and guarantee the installation back and the clearance between the long locking plate, two angle of bending department are greater than two angle of bending department of long locking plate when the delivery state to produce bigger elastic force under the restriction of turbine disk hangers and blade flange fender ear.
When the locking plate is installed, 4 long locking plates and 1 short locking plate are installed in sequence.
In the process of assembling the long locking plates, the bent edge faces outwards, the circular notches are pushed to enable the 4 long locking plates to be in butt joint and tightly pushed, and meanwhile, the edges of the long locking plates are guaranteed to be located in the middle positions of the tenon end faces of the blades, as shown in fig. 5, wherein a is a schematic diagram of head-to-tail pushing of the four long locking plates, and b is a schematic diagram of the positions of the edges of the long locking plates relative to the blades.
When assembling the short locking plate, firstly, the short locking plate needs to be repaired, and the width of the gap between the short locking plate and the first long locking plate is about 0.4mm, as shown in fig. 6 c. When the locking device is installed, one surface of the middle protrusion faces outwards and is placed between the blade flange plate hanging lug and the turbine disc hanging lug as shown in fig. 6a, and then the protruding part of the short locking plate is knocked flat by a soft hammer to achieve the locking effect as shown in fig. 6 b.
The effect of all the locking pieces after assembly is shown in fig. 7, when viewed from the exhaust side (fig. 7b), the locking pieces form a full circle structure, and an axial locking state is achieved under the action of the installation angle of the blade and the elastic force of the locking pieces; from the side observation that admits air, along the tensile direction of tenon tooth, can see that the gap between the locking plate just in time is in the intermediate position of blade tenon terminal surface, and the circular arc breach is located blade tenon terminal surface department (fig. 7a, fig. 7c), has avoided tongue-and-groove bottom space, and the leakage volume that the gap caused can be neglected basically. Like this, the space of tongue-and-groove bottom and the space of blade flange below all are blocked by the locking piece to can prevent that the gas from leaking from tongue-and-groove bottom and blade flange below.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (8)
1. A turbine blade locking device is characterized in that the device is used for axially limiting blades of a high-pressure turbine so as to lock the blades on a turbine disc and simultaneously play a role of a wind shield.
2. the apparatus of claim 1 wherein the turbine blade locking means comprises a full circle locking tab disposed between the blade platform lug and the turbine disk lug; gaps among the locking plates are positioned in the middle of the tenon end faces of the blades, if the number of the blades is 47, the circumferential angle of each blade is 7.66 degrees, the whole circle of locking plates consists of 4 long locking plates and 1 short locking plate which are connected end to end, each long locking plate covers 11 blades, 4 long locking plates continuously cover 44 blades, and the short locking plates cover the rest 3 blades; the circumferential angle of the long locking plate is designed to be 84.3 degrees; the circumferential angle of the short locking tab is set to 24 °.
3. The device as claimed in claim 1, wherein the projection of the long locking piece is fan-shaped and has two bending parts, and an arc notch is formed at one end of the middle diameter part of the long locking piece and is positioned at the tenon end surface of the blade.
4. The device of claim 1, wherein the short locking tab has two bends, and wherein the short locking tab has an intermediate formed condition in which the intermediate portion of the two bends is bent and a delivery condition in which the two bends are bent at an angle greater than the angle of the two bends of the long locking tab.
5. A method of assembling the device of claim 4, wherein, when assembling, 4 long locking pieces and 1 short locking piece are installed in sequence; in the process of assembling the long locking plate, the bent edge faces outwards, the arc notch is pushed to enable the 4 long locking plates to be in butt joint and tightly pushed, and meanwhile, the edge of the long locking plate is located in the middle of the tenon end face of the blade; when assembling short locking plate, at first repair short locking plate, guarantee that the gap width between short locking plate and the first long locking plate is at the certain limit, during the installation, middle bellied one side is outwards placed between blade flange hangers and turbine disc hangers, then strikes the flat with the bellied position of short locking plate with soft hammer.
6. The method of claim 5, wherein the raised portion of the short locking tab is struck flat with a soft hammer during assembly.
7. The method of claim 5, wherein the short locking tab is trimmed to ensure that the gap between the short locking tab and the first long locking tab is 0.4mm wide.
8. Use of the device according to any one of claims 1 to 4 in a high-pressure turbine having a chamfered transition space at the bottom of the turbine disk mortise.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911040476.7A CN110578557A (en) | 2019-10-29 | 2019-10-29 | Turbine blade locking device and assembling method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911040476.7A CN110578557A (en) | 2019-10-29 | 2019-10-29 | Turbine blade locking device and assembling method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110578557A true CN110578557A (en) | 2019-12-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911040476.7A Pending CN110578557A (en) | 2019-10-29 | 2019-10-29 | Turbine blade locking device and assembling method thereof |
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| Country | Link |
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| CN (1) | CN110578557A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114076000A (en) * | 2020-08-17 | 2022-02-22 | 中国航发商用航空发动机有限责任公司 | Blade axial limiting device, blade disc structure and gas turbine |
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| US20060239822A1 (en) * | 2004-11-13 | 2006-10-26 | Joachim Wulf | Apparatus and method for anchoring a rotor blade in a rotor of a turbo machine |
| CN101517200A (en) * | 2006-09-25 | 2009-08-26 | 西门子公司 | Turbine rotor with locking plates and corresponding assembly method |
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| US20140356175A1 (en) * | 2013-05-31 | 2014-12-04 | Rolls-Royce Plc | Lock plate |
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| US20150260050A1 (en) * | 2014-03-14 | 2015-09-17 | Honda Motor Co., Ltd. | Turbine wheel |
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- 2019-10-29 CN CN201911040476.7A patent/CN110578557A/en active Pending
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| US20060239822A1 (en) * | 2004-11-13 | 2006-10-26 | Joachim Wulf | Apparatus and method for anchoring a rotor blade in a rotor of a turbo machine |
| CN101517200A (en) * | 2006-09-25 | 2009-08-26 | 西门子公司 | Turbine rotor with locking plates and corresponding assembly method |
| CN101529052A (en) * | 2006-10-26 | 2009-09-09 | 西门子公司 | Turbine blade assembly |
| CN101836018A (en) * | 2007-10-25 | 2010-09-15 | 西门子公司 | Turbine blade assembly and seal strip |
| CN102203389A (en) * | 2008-10-30 | 2011-09-28 | 西门子公司 | Gas turbine having sealing plates on the turbine disc |
| US20140356175A1 (en) * | 2013-05-31 | 2014-12-04 | Rolls-Royce Plc | Lock plate |
| US20150260050A1 (en) * | 2014-03-14 | 2015-09-17 | Honda Motor Co., Ltd. | Turbine wheel |
| CN104329123A (en) * | 2014-11-28 | 2015-02-04 | 哈尔滨广瀚燃气轮机有限公司 | Novel movable blade and wheel disc fixing structure of turbine engine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114076000A (en) * | 2020-08-17 | 2022-02-22 | 中国航发商用航空发动机有限责任公司 | Blade axial limiting device, blade disc structure and gas turbine |
| CN114076000B (en) * | 2020-08-17 | 2024-05-07 | 中国航发商用航空发动机有限责任公司 | Blade axial limiting device, blade disc structure and gas turbine |
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Application publication date: 20191217 |