CN107524477A - For eliminating the instrument and method of High Pressure Turbine Rotor blade joint gap - Google Patents
For eliminating the instrument and method of High Pressure Turbine Rotor blade joint gap Download PDFInfo
- Publication number
- CN107524477A CN107524477A CN201610444115.9A CN201610444115A CN107524477A CN 107524477 A CN107524477 A CN 107524477A CN 201610444115 A CN201610444115 A CN 201610444115A CN 107524477 A CN107524477 A CN 107524477A
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- CN
- China
- Prior art keywords
- rotor blade
- joint gap
- pressure turbine
- high pressure
- screw rod
- 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.)
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a kind of instrument and method for being used to eliminate High Pressure Turbine Rotor blade joint gap, the instrument includes adjusting screw rod, upper drive block, extrusion block and lower drive block, and the upper drive block, the extrusion block and the lower drive block are located on the adjusting screw rod successively；When turning the adjusting screw rod, the upper drive block guides the adjusting screw rod to rotate, and is pressed down against the extrusion block, and the lower drive block guides the adjusting screw rod to rotate, the upward extrusion block so that the extrusion block is outwardly.Methods described is using the instrument for being used to eliminate High Pressure Turbine Rotor blade joint gap as described above, the present invention, which is used for the instrument for eliminating High Pressure Turbine Rotor blade joint gap and method, can effectively eliminate the joint gap of high-pressure turbine working blade and the turbine disk, so as to realize accurate acquisition high-pressure turbine blade tip diameter.The principle of the invention is simple, and tool construction is simple, and manufacture and maintenance cost are relatively low.
Description
Technical field
It is more particularly to a kind of to be used to eliminate high-pressure turbine turn the present invention relates to aero-engine assembling manufacturing field
The instrument and method of blades joint gap.
Background technology
High Pressure Turbine Rotor cell cube is the main acting part of aero-engine, typically by drum barrel, seal pan,
The turbine disk, rotor blade, rear baffle, rear axle etc. form.Turbine turns the gap (tip clearance) between stator
The acting characteristic of turbine is directly affected, so as to influence the overall performance of engine.
In the prior art, excessive tip clearance can reduce turbine efficiency, so as to cause Thrust specific fuel consumption
Increase and fuel gas temperature rise.Too small tip clearance can cause turbo blade to be scraped mutually with casing inwall
Rub, cause vibration.In order to control blade and casing gap, ensure performance and security, it is necessary to control cold conditions
Tip clearance ensures the best clearance value under working condition, and under cold conditions tip clearance need it is by measuring high
Pressure turbine rotor blade tip diameter and casing internal diameter obtain after calculating, and the measured value of blade tip diameter must be accurate.
High-pressure turbine working blade is inserted by fir shape tenon in the fir shape groove of the turbine disk, tenon and tongue-and-groove
Between certain gap be present.For accurate measurement high-pressure turbine blade tip diameter, need outwards to exclude blade before measurement
Joint gap between disk.Traditional way for outwards excluding blade joint gap is to pinch blade by human hand
Leaf basin and blade back, outside force, blade joint gap reduces in the presence of outer drag.Or knife will be solved
Insertion tongue-and-groove simultaneously props up root of blade, is reduced by solving the external prying force between knife and the turbine disk between blade connection
Gap.Human factor has a great influence in whole process, and the size that exerts a force and direction vary with each individual, blade joint gap
It is difficult to be eliminated, cause the measured value of blade tip diameter extremely unstable, the exact value of blade tip diameter can not be obtained.
The measurement of High Pressure Turbine Rotor blade tip diameter is typically carried out in engine assembly or decomposition.
The content of the invention
The technical problem to be solved in the present invention is to overcome interlobate of High Pressure Turbine Rotor in the prior art
Gap can reduce the defects of turbine efficiency, there is provided a kind of work for being used to eliminate High Pressure Turbine Rotor blade joint gap
Tool and method.
The present invention is that solve above-mentioned technical problem by following technical proposals：One kind is used to eliminate high pressure whirlpool
The instrument of rotor blades joint gap, its feature be, the instrument include adjusting screw rod, upper drive block,
Block and lower drive block are extruded, the upper drive block, the extrusion block and the lower drive block are located in institute successively
State on adjusting screw rod；
When turning the adjusting screw rod, the upper drive block guides the adjusting screw rod to rotate, and is pressed down against
The extrusion block, the lower drive block guide the adjusting screw rod to rotate, the upward extrusion block, made
It is outwardly to obtain the extrusion block.
It is preferred that the extrusion block and the upper drive block and the lower drive block contact surface are inclined-plane, institute
The inclination angle for stating inclined-plane is 30 ° -60 °.
It is preferred that the extrusion block is wedge shaped or trapezoidal.
It is preferred that offering a sliding groove among the extrusion block, the adjusting screw rod is located in the slip
In groove so that the extrusion block can move left and right along the adjusting screw rod.
Present invention also offers a kind of method for eliminating High Pressure Turbine Rotor blade joint gap, its feature
It is, methods described uses is used for the instrument for eliminating High Pressure Turbine Rotor blade joint gap as described above,
It the described method comprises the following steps：
S1, the assembling instrument for being used to eliminate High Pressure Turbine Rotor blade joint gap；
S2, by it is described be used to eliminating the instrument of High Pressure Turbine Rotor blade joint gap be vertically put into the turbine disk
In the end tongue-and-groove seam of rotor blade；
S3, the adjustment posture for being used to eliminate the instrument of High Pressure Turbine Rotor blade joint gap, to eliminate
Joint gap between the rotor blade of the turbine disk.
It is preferred that the step S1In it is further comprising the steps of：
S11, by upper drive block, extrusion block and lower drive block be located in successively on adjusting screw rod；
S12, unscrew the adjusting screw rod so that it is described extrusion block be in contraction state；
It is preferred that the step S3It is further comprising the steps of：
S31, the adjustment instrument for being used to eliminate High Pressure Turbine Rotor blade joint gap so that the upper drive
The inner face of motion block, the extrusion block and the lower drive block is bonded with the turbine disc mortise inner face；
S32, tighten the adjusting screw rod so that it is described extrusion block along corresponding to inclined-plane swell, push against the whirlpool
The blade root inner surface of the rotor blade of wheel disc；
S33, continue to tighten the adjusting screw rod, the rotor blade of the turbine disk described in outside tensioner, described in elimination
The joint gap of the rotor blade of the turbine disk.
The positive effect of the present invention is：
The present invention, which is used for the instrument for eliminating High Pressure Turbine Rotor blade joint gap and method, effectively to disappear
Except high-pressure turbine working blade and the joint gap of the turbine disk, so as to realize that accurate acquisition high-pressure turbine blade tip is straight
Footpath.The principle of the invention is simple, and tool construction is simple, and manufacture and maintenance cost are relatively low.
Brief description of the drawings
The present invention the above and other feature, property and advantage will be by with reference to the accompanying drawings and examples
Description and become apparent, identical reference represents identical feature all the time in the accompanying drawings, wherein：
Fig. 1 is that the present invention is under contraction state for eliminating the instrument of High Pressure Turbine Rotor blade joint gap
Structural representation.
Fig. 2 is that the present invention is under spreading state for eliminating the instrument of High Pressure Turbine Rotor blade joint gap
Structural representation.
Fig. 3 is the scheme of installation that the present invention is used to eliminate the instrument of High Pressure Turbine Rotor blade joint gap.
Embodiment
For the above objects, features and advantages of the present invention can be become apparent, below in conjunction with accompanying drawing to this hair
Bright embodiment elaborates.
Embodiments of the invention are described with detailed reference to accompanying drawing now.Now with detailed reference to the preferred of the present invention
Embodiment, its example are shown in the drawings.In the case of any possible, phase will be used in all of the figs
With mark represent same or analogous part.In addition, although the term used in the present invention is from public affairs
Know what is selected in public term, but some terms mentioned in description of the invention are probably applicant
Carry out selection by his or her judgement, its detailed meanings illustrates in the relevant portion of description herein.In addition,
It is required that not only by used actual terms, and the meaning for being also to be contained by each term is managed
The solution present invention.
Fig. 1 is that the present invention is under contraction state for eliminating the instrument of High Pressure Turbine Rotor blade joint gap
Structural representation.Fig. 2 is that the present invention is in for eliminating the instrument of High Pressure Turbine Rotor blade joint gap
Structural representation under spreading state.Fig. 3 is used to eliminate High Pressure Turbine Rotor blade joint gap for the present invention
Instrument scheme of installation.
As shown in Figure 1 to Figure 3, the invention discloses one kind be used for eliminate High Pressure Turbine Rotor blade connection between
The instrument 10 of gap, it includes adjusting screw rod 11, upper drive block 12, extrusion block 13 and lower drive block 14,
Upper drive block 12, extrusion block 13 and lower drive block 14 are located on adjusting screw rod 11 successively.When turning
During adjusting screw rod 11, the upper guide adjustment screw rod 11 of drive block 12 rotates, and is pressed down against extruding block 13, under
The guide adjustment screw rod 11 of drive block 14 rotates, upward extrusion block 13 so that the extrusion convex of block 13
Go out.
Preferably, the contact surface extruded between block 13 and upper drive block 12 is arranged to inclined-plane, extrudes block 13
Contact surface between lower drive block 14 is also configured as inclined-plane, and the inclination angle on inclined-plane is preferably 30 ° -60 ° herein.
Especially, such as extrusion block 13 is preferably wedge shaped or trapezoidal.Splayed double inclined plane is set on extrusion block,
Gradient is equal, and power is screwed for transmit screw rod, act on extrusion block 13 to make a concerted effort be horizontal direction,
Driving extrusion block 13 is swelled and shunk.
Meanwhile a sliding groove 15 is offered in the centre of extrusion block 13, adjusting screw rod 11 is located in slip
In groove 15 so that extrusion block 13 can move left and right along adjusting screw rod 11.For example, on extrusion block 13
Bar hole is set so that extrusion block 13 can be swelled and shunk in bar hole.
According to said structure, it is used to eliminate High Pressure Turbine Rotor blade joint gap present invention also offers one kind
Method, it uses the as described above instrument 10 for being used to eliminate High Pressure Turbine Rotor blade joint gap, institute
The method of stating comprises the following steps：
Step S1, assemble instrument 10 for eliminating High Pressure Turbine Rotor blade joint gap.
Specifically, the step S1In it is further comprising the steps of：
First, upper drive block 12, extrusion block 13 and lower drive block 14 are located in adjusting screw rod 11 successively
On；
Secondly, adjusting screw rod 11 is unscrewed so that extrusion block 13 is in contraction state.
Step S2, will vertically be put into turbine for the instrument 10 for eliminating High Pressure Turbine Rotor blade joint gap
In the end tongue-and-groove seam of the rotor blade 21 of disk 20.
Step S3, adjust the posture of instrument 10 for eliminating High Pressure Turbine Rotor blade joint gap, with
Eliminate the joint gap between the rotor blade 21 of the turbine disk 20.
Specifically, the step S3It is further comprising the steps of：
First, the instrument 10 for eliminating High Pressure Turbine Rotor blade joint gap is adjusted so that upper drive block
12nd, extrude block 13 and the inner face of lower drive block 14 is bonded with the tongue-and-groove inner face of the turbine disk 20；
Secondly, adjusting screw rod 11 is tightened so that extrusion block 13 swells along corresponding inclined-plane, pushes against the turbine disk
The blade root inner surface of 20 rotor blade 21；
Then, continue to tighten adjusting screw rod 11, the rotor blade 21 of the outside tensioner turbine disk 20, eliminate whirlpool
The joint gap of the rotor blade 21 of wheel disc 20.
The present invention is used for the instrument for eliminating High Pressure Turbine Rotor blade joint gap and method passes through built-in bulging work
Tool produces extruding force to eliminate the joint gap of moving turbine blade.Specifically, its tightening by screw rod
Control extrusion block swells, and passes through the contraction for unscrewing control extrusion block of screw rod.
In summary, the present invention is used for the instrument for eliminating High Pressure Turbine Rotor blade joint gap and method can be with
The joint gap of high-pressure turbine working blade and the turbine disk is effectively eliminated, so as to realize accurate acquisition high pressure whirlpool
Vane tip diameter.The principle of the invention is simple, and tool construction is simple, and manufacture and maintenance cost are relatively low.
Although the foregoing describing the embodiment of the present invention, it will be appreciated by those of skill in the art that
These are merely illustrative of, and protection scope of the present invention is defined by the appended claims.This area
Technical staff can make more on the premise of without departing substantially from the principle and essence of the present invention to these embodiments
Kind change or modification, but these changes and modification each fall within protection scope of the present invention.
Claims (7)
- A kind of 1. instrument for being used to eliminate High Pressure Turbine Rotor blade joint gap, it is characterized in that, the instrument includes adjusting screw rod, upper drive block, extrusion block and lower drive block, and the upper drive block, the extrusion block and the lower drive block are located on the adjusting screw rod successively；When turning the adjusting screw rod, the upper drive block guides the adjusting screw rod to rotate, and is pressed down against the extrusion block, and the lower drive block guides the adjusting screw rod to rotate, the upward extrusion block so that the extrusion block is outwardly.
- 2. the instrument as claimed in claim 1 for being used to eliminate High Pressure Turbine Rotor blade joint gap, it is characterised in that the extrusion block and the upper drive block and the lower drive block contact surface are inclined-plane, and the inclination angle on the inclined-plane is 30 ° -60 °.
- 3. the instrument as claimed in claim 2 for being used to eliminate High Pressure Turbine Rotor blade joint gap, it is characterised in that the extrusion block is wedge shaped or trapezoidal.
- 4. the instrument as claimed in claim 3 for being used to eliminate High Pressure Turbine Rotor blade joint gap, it is characterized in that, a sliding groove is offered among the extrusion block, the adjusting screw rod is located in the sliding groove so that the extrusion block can move left and right along the adjusting screw rod.
- A kind of 5. method for eliminating High Pressure Turbine Rotor blade joint gap, it is characterised in that methods described the described method comprises the following steps using the instrument for being used to eliminate High Pressure Turbine Rotor blade joint gap as described in claim 1-4 any one：S1, the assembling instrument for being used to eliminate High Pressure Turbine Rotor blade joint gap；S2, the instrument for being used to eliminating High Pressure Turbine Rotor blade joint gap is vertically put into the turbine disk rotor blade end tongue-and-groove seam in；S3, the adjustment posture for being used to eliminate the instrument of High Pressure Turbine Rotor blade joint gap, to eliminate the joint gap between the rotor blade of the turbine disk.
- 6. the method as claimed in claim 5 for being used to eliminate High Pressure Turbine Rotor blade joint gap, it is characterised in that the step S1In it is further comprising the steps of：S11, by upper drive block, extrusion block and lower drive block be located in successively on adjusting screw rod；S12, unscrew the adjusting screw rod so that it is described extrusion block be in contraction state.
- 7. the method as claimed in claim 5 for being used to eliminate High Pressure Turbine Rotor blade joint gap, it is characterised in that the step S3It is further comprising the steps of：S31, the adjustment instrument for being used to eliminate High Pressure Turbine Rotor blade joint gap so that the inner face of the upper drive block, the extrusion block and the lower drive block is bonded with the turbine disc mortise inner face；S32, tighten the adjusting screw rod so that it is described extrusion block along corresponding to inclined-plane swell, push against the blade root inner surface of the rotor blade of the turbine disk；S33, continue to tighten the adjusting screw rod, the rotor blade of the turbine disk described in outside tensioner, eliminate the joint gap of the rotor blade of the turbine disk.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610444115.9A CN107524477B (en) | 2016-06-20 | 2016-06-20 | For eliminating the tool and method of High Pressure Turbine Rotor blade joint gap |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610444115.9A CN107524477B (en) | 2016-06-20 | 2016-06-20 | For eliminating the tool and method of High Pressure Turbine Rotor blade joint gap |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107524477A true CN107524477A (en) | 2017-12-29 |
| CN107524477B CN107524477B (en) | 2019-07-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610444115.9A Active CN107524477B (en) | 2016-06-20 | 2016-06-20 | For eliminating the tool and method of High Pressure Turbine Rotor blade joint gap |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108050913A (en) * | 2017-12-14 | 2018-05-18 | 中国航发沈阳发动机研究所 | A kind of measuring device for turbine rotor outer diameter |
| CN108397455A (en) * | 2018-02-06 | 2018-08-14 | 彭志军 | A kind of expansion fixed connection structure of household handware |
| CN109238125A (en) * | 2018-08-09 | 2019-01-18 | 中国航发沈阳发动机研究所 | Blade displacement adjustment controlling means and control system |
| CN112372451A (en) * | 2020-11-05 | 2021-02-19 | 中国航发哈尔滨东安发动机有限公司 | High-precision rotor blade and rim size control method thereof |
| CN114263632A (en) * | 2021-10-22 | 2022-04-01 | 中国航发沈阳发动机研究所 | Rotor component of engine fan |
| CN118081543A (en) * | 2024-04-26 | 2024-05-28 | 国营川西机器厂 | Blade tip grinding tenon tightening device for high-pressure turbine blade of aero-engine |
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| JP2000136925A (en) * | 1998-10-30 | 2000-05-16 | Mitsubishi Heavy Ind Ltd | Rotating device and contact-type sensor |
| CN102853743A (en) * | 2012-08-24 | 2013-01-02 | 江苏省徐州锻压机床厂集团有限公司 | Mechanism for measuring longitudinal gap of connecting rod screw thread |
| CN203955785U (en) * | 2014-06-30 | 2014-11-26 | 马鞍山市沪东重工机械制造有限公司 | A kind of bender that adopts single upper wedge to compensate |
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2016
- 2016-06-20 CN CN201610444115.9A patent/CN107524477B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000136925A (en) * | 1998-10-30 | 2000-05-16 | Mitsubishi Heavy Ind Ltd | Rotating device and contact-type sensor |
| CN102853743A (en) * | 2012-08-24 | 2013-01-02 | 江苏省徐州锻压机床厂集团有限公司 | Mechanism for measuring longitudinal gap of connecting rod screw thread |
| CN203955785U (en) * | 2014-06-30 | 2014-11-26 | 马鞍山市沪东重工机械制造有限公司 | A kind of bender that adopts single upper wedge to compensate |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108050913A (en) * | 2017-12-14 | 2018-05-18 | 中国航发沈阳发动机研究所 | A kind of measuring device for turbine rotor outer diameter |
| CN108397455A (en) * | 2018-02-06 | 2018-08-14 | 彭志军 | A kind of expansion fixed connection structure of household handware |
| CN109238125A (en) * | 2018-08-09 | 2019-01-18 | 中国航发沈阳发动机研究所 | Blade displacement adjustment controlling means and control system |
| CN109238125B (en) * | 2018-08-09 | 2020-08-11 | 中国航发沈阳发动机研究所 | Blade displacement calibration control method and control system |
| CN112372451A (en) * | 2020-11-05 | 2021-02-19 | 中国航发哈尔滨东安发动机有限公司 | High-precision rotor blade and rim size control method thereof |
| CN114263632A (en) * | 2021-10-22 | 2022-04-01 | 中国航发沈阳发动机研究所 | Rotor component of engine fan |
| CN118081543A (en) * | 2024-04-26 | 2024-05-28 | 国营川西机器厂 | Blade tip grinding tenon tightening device for high-pressure turbine blade of aero-engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107524477B (en) | 2019-07-05 |
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Effective date of registration: 20190808 Address after: Room 301, No. 1, 600 Xinyuan South Road, Lingang New Town, Pudong New Area, Shanghai, 20106 Co-patentee after: China Hangfa commercial aviation engine limited liability company Patentee after: China Hangfa Shanghai Aero Engine Manufacturing Co. Ltd. Address before: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee before: China Hangfa commercial aviation engine limited liability company |