CN111895951B - Method for detecting outer diameter of turbine rotor blade - Google Patents
Method for detecting outer diameter of turbine rotor blade Download PDFInfo
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- CN111895951B CN111895951B CN202010989799.7A CN202010989799A CN111895951B CN 111895951 B CN111895951 B CN 111895951B CN 202010989799 A CN202010989799 A CN 202010989799A CN 111895951 B CN111895951 B CN 111895951B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/10—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring diameters
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Abstract
The invention discloses a method for detecting the outer diameter of a turbine rotor blade, and belongs to the technical field of aero-engines. The method comprises the following steps: the taper bolt and the sealing labyrinth plate are dismounted from the turbine rotor; step two: one end of the jacking component is plugged into a gap between the bottom of the tenon of the high-pressure turbine blade and the mortise of the high-pressure turbine disc; step three: the mounting disc is mounted on a high-pressure turbine disc through a taper bolt, and a force application assembly is arranged on the high-pressure turbine disc at a position corresponding to the jacking assembly; step four: a force along the axial direction of the turbine shaft is applied to the jacking assembly through the force application assembly, the axial force is converted into a radial force through the jacking assembly, and the tenon of the high-pressure turbine blade is tightly jacked with the mortise of the high-pressure turbine disc without clearance. On the basis of the original part of the turbine rotor, the state of the high-pressure turbine blade under the action of centrifugal force can be simulated by adopting simple parts, and the device has the advantages of simplicity in operation, easiness in realization, low cost and the like.
Description
Technical Field
The invention relates to a method for detecting the outer diameter of a turbine rotor blade, and belongs to the technical field of aero-engines.
Background
With the gradual maturity of aeroengine technology, the manufacturing requirement on an engine rotor is higher and higher, the engine high-pressure turbine rotor is used as a core component of the engine, and the high-pressure turbine rotor and a corresponding casing have extremely high clearance requirement during working. Once the clearance is too large, the engine gas will be leaked, and the engine efficiency will be reduced, and once the clearance is too small, the turbine rotor rotating at high speed will rub against the casing, so it is important to control the clearance between the turbine rotor and the casing. The manufacturing process and the final working state of the turbine rotor of the engine have larger working condition difference, the turbine rotor rotates at high speed in the working state, and the outer diameter of the rotor is larger than that of the rotor in a free state in the manufacturing process due to the extremely large centrifugal force, so that the clearance between the blade tip and the casing of the high-pressure turbine rotor is difficult to control.
The invention provides a method for detecting the outer diameter of a turbine rotor blade, which simulates the state of the blade subjected to centrifugal force to detect the outer diameter of the blade and conveniently provides reference for better controlling the clearance between a turbine rotor and a casing.
Disclosure of Invention
In order to solve the technical problem, the invention provides a method for detecting the outer diameter of a turbine rotor blade.
The invention is realized by the following technical scheme:
the method for detecting the outer diameter of the turbine rotor blade comprises a turbine shaft, a high-pressure turbine disc and a sealing labyrinth disc, wherein a rear shaft neck is arranged on the outer circle of the turbine shaft, the high-pressure turbine disc and the sealing labyrinth disc are connected with the rear shaft neck through taper bolts, the high-pressure turbine disc is located between the sealing labyrinth disc and the rear shaft neck, a plurality of high-pressure turbine blades are arranged on the high-pressure turbine disc, and the method for detecting the outer diameter of the turbine rotor blade comprises the following steps:
the method comprises the following steps: the taper bolt and the sealing labyrinth disc are dismounted from the turbine rotor,
step two: one end of the jacking component is plugged into a gap between the bottom of the tenon of the high-pressure turbine blade and the mortise of the high-pressure turbine disc,
step three: the mounting disc is mounted on the high-pressure turbine disc through the taper bolt, a force application assembly is arranged on the high-pressure turbine disc at a position corresponding to the jacking assembly,
step four: the force application component applies a force along the axial direction of the turbine shaft to the jacking component, the jacking component converts the axial force into a radial force, the tenon of the high-pressure turbine blade is tightly jacked with the mortise of the high-pressure turbine disc without clearance,
step five: and detecting the outer diameter of the high-pressure turbine blade, and judging whether the clearance between the high-pressure turbine blade and the casing is qualified.
The whole jacking assembly is of a T-shaped structure.
And an included angle between the jacking assembly and the axis of the turbine shaft is an acute angle.
The jacking assembly comprises an inclined wedge block A and an inclined wedge block B, the inclined wedge block A is in contact with the high-pressure turbine disc, the inclined wedge block B is in contact with the high-pressure turbine blade, the inclined wedge block B is mutually attached to the inclined wedge block A, and the upper portions of the attaching surfaces of the inclined wedge block A and the inclined wedge block B are inclined towards the direction far away from the turbine shaft.
One surface of the inclined wedge block A, which is far away from the inclined wedge block B, is an arc surface, and the arc surface partially extends into a gap between the bottom of the tenon of the high-pressure turbine blade and the mortise of the high-pressure turbine disc.
The installation position of the force application component on the installation disc corresponds to the inclined wedge block A.
And the force application assembly is in threaded connection with the mounting disc.
The force application component is a screw, and the axis of the screw is parallel to the axis of the turbine shaft.
The mounting position of mounting disc is the same with the labyrinth dish of obturating, and plays the effect that is used for simulating the labyrinth dish of obturating.
The invention has the beneficial effects that:
1. the method is characterized in that an axial force is applied to a slanting wedge A through a screw, and a radial force is applied to a slanting wedge B through the slanting wedge A, so that a tenon of the high-pressure turbine blade is tightly abutted against a mortise of a high-pressure turbine disc without clearance, the outer diameter of the high-pressure turbine blade at the moment is measured, and the clearance between a turbine rotor and a casing is controlled.
2. On the basis of the original parts of the turbine rotor, the state of the high-pressure turbine blade under the action of centrifugal force can be simulated by adopting simple parts, and the device has the advantages of simplicity in operation, easiness in implementation, low cost and the like.
Drawings
FIG. 1 is a schematic structural view of a turbine rotor of the present invention;
FIG. 2 is a schematic view of the assembly of the turbine rotor with the mounting plate, the jacking assembly and the force application assembly of the present invention;
FIG. 3 is a schematic view of the assembly of the high pressure turbine disk and high pressure turbine blades of the present invention;
FIG. 4 is a schematic structural view of the tightening unit of the present invention;
FIG. 5 is a rotational cross-sectional view taken along line B-B of FIG. 4;
fig. 6 is a rotated cross-sectional view taken along a-a of fig. 4.
In the figure: the device comprises a 1-turbine shaft, a 2-rear shaft neck, a 3-high-pressure turbine disc, a 4-sealing labyrinth disc, a 5-high-pressure turbine blade, a 6-taper bolt, a 7-mounting disc, an 8-inclined wedge block A, a 9-inclined wedge block B and a 10-screw.
Detailed Description
The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.
As shown in fig. 1 to 6, the method for detecting the outer diameter of the turbine rotor blade according to the present invention includes a turbine shaft 1, a high-pressure turbine disc 3 and a sealing labyrinth disc 4, wherein a rear journal 2 is disposed on an outer circle of the turbine shaft 1, the high-pressure turbine disc 3 and the sealing labyrinth disc 4 are connected to the rear journal 2 through a taper bolt 6, the high-pressure turbine disc 3 is located between the sealing labyrinth disc 4 and the rear journal 2, a plurality of high-pressure turbine blades 5 are disposed on the high-pressure turbine disc 3, and the method for detecting the outer diameter of the turbine rotor blade includes the following steps:
the method comprises the following steps: and (4) detaching the taper bolt 6 and the sealing labyrinth plate 4 from the turbine rotor.
Step two: one end of the jacking component is inserted into a gap between the bottom of the tenon of the high-pressure turbine blade 5 and the mortise of the high-pressure turbine disc 3.
Step three: the mounting disc 7 is mounted on the high-pressure turbine disc 3 through the taper bolts 6, and a force application assembly is arranged on the high-pressure turbine disc 3 at a position corresponding to the jacking assembly.
Step four: a force along the axial direction of the turbine shaft 1 is applied to the jacking assembly through the force application assembly, and the axial force is converted into a radial force through the jacking assembly, so that the tenon of the high-pressure turbine blade 5 is jacked tightly without clearance with the mortise of the high-pressure turbine disc 3.
Step five: and detecting the outer diameter of the high-pressure turbine blade 5, and judging whether the gap between the high-pressure turbine blade 5 and the casing is qualified.
In use, the clearance between the turbine rotor and the casing is controlled, in essence the clearance between the high pressure turbine blades 5 and the casing in the operating condition. When the aircraft engine works, the turbine rotor runs at a high speed, and the tenon of the high-pressure turbine blade 5 abuts against the mortise of the high-pressure turbine disc 3 without clearance under the action of centrifugal force. Therefore, according to the method for detecting the outer diameter of the turbine rotor blade provided by the invention, a force along the axial direction of the turbine shaft 1 is applied to the jacking assembly through the force application assembly, the axial force is converted into a radial force through the jacking assembly, the tenon of the high-pressure turbine blade 5 is jacked tightly with the mortise of the high-pressure turbine disc 3 without clearance, and the state of the high-pressure turbine blade 5 under the action of centrifugal force is essentially simulated, so that the outer diameter of the high-pressure turbine blade 5 at the moment is measured, and the clearance between the turbine rotor and the casing is controlled.
The whole jacking assembly is of a T-shaped structure. The force application component can apply force to the jacking component conveniently.
An included angle between the jacking assembly and the axis of the turbine shaft 1 is an acute angle. Because the mortise of the high-pressure turbine disc 3 has a certain angle with the axis of the turbine shaft 1, the jacking component is also designed into a corresponding angle.
The jacking assembly comprises inclined wedges A8 and inclined wedges B9, the inclined wedges A8 are in contact with the high-pressure turbine disc 3, the inclined wedges B9 are in contact with the high-pressure turbine blade 5, the inclined wedges B9 are attached to the inclined wedges A8, and the upper portions of the attaching surfaces of the inclined wedges A and the inclined wedges B are inclined towards the direction far away from the turbine shaft 1. After the inclined wedge block A8 is subjected to the axial force of the screw 10, the axial force is resolved into a radial force to be applied to the inclined wedge block B9, so that the tenon of the high-pressure turbine blade 5 is tightly abutted with the mortise of the high-pressure turbine disc 3 without clearance.
One of the faces of the inclined wedges A8 remote from the inclined wedges B9 is a radiused surface that extends partially into the gap between the base of the tenons of the high pressure turbine blades 5 and the mortises of the high pressure turbine disk 3. Because the bottom surface of the mortise of the high-pressure turbine disc 3 is in a circular arc structure, one surface of the inclined wedge block A8 is also designed to be a corresponding circular arc surface.
The installation position of the force application component on the installation plate 7 corresponds to the inclined wedge A8.
The force application component is in threaded connection with the mounting plate 7.
The force application component is a screw 10, and the axis of the screw 10 is parallel to the axis of the turbine shaft 1.
The mounting position of the mounting plate 7 is the same as that of the sealing labyrinth plate 4, and the mounting plate plays a role in simulating the sealing labyrinth plate 4.
Specifically, as shown in fig. 1, the tenon of the high-pressure turbine blade 5 is abutted against the mortise of the high-pressure turbine disc 3 without clearance, and the only available space is the space between the bottom of the tenon of the high-pressure turbine blade 5 and the mortise of the high-pressure turbine disc 3, as shown in fig. 3, the space is a square space with a width of 5mm, and is small, so that a mechanism capable of generating radial force is difficult to accommodate.
In use, each high pressure turbine blade 5 has a corresponding mortise in the high pressure turbine disk 3, each requiring a set of wedges, so 41 sets of wedges are required for the entire turbine rotor. The invention applies axial force to 41 groups of inclined wedges to ensure that the jacking degree of each high-pressure turbine blade 5 is the same, and adopts 41 groups of screws 10, wherein each group of inclined wedges corresponds to one screw 10, and force is respectively applied to each group of inclined wedges through the screws 10.
Compared with the prior art, the method for detecting the outer diameter of the turbine rotor blade has the following beneficial effects:
1. the outer diameter of the high pressure turbine blade 5 at this time is measured by applying an axial force to the skewed wedge block A8 through the screw 10, resolving the axial force by the skewed wedge block A8 to apply a radial force to the skewed wedge block B9, thereby tightening the tenon of the high pressure turbine blade 5 against the mortise of the high pressure turbine disk 3 without clearance, so as to control the clearance between the turbine rotor and the casing.
2. On the basis of the original parts of the turbine rotor, the state of the high-pressure turbine blade 5 under the action of centrifugal force can be simulated by adopting simple parts, and the method has the advantages of simple operation, easy realization, low cost and the like.
Claims (5)
1. A method of detecting an outer diameter of a turbine rotor blade, comprising: the turbine rotor comprises a turbine shaft (1), a high-pressure turbine disc (3) and a sealing labyrinth disc (4), a rear shaft neck (2) is arranged on the outer circle of the turbine shaft (1), the high-pressure turbine disc (3) and the sealing labyrinth disc (4) are connected with the rear shaft neck (2) through taper bolts (6), the high-pressure turbine disc (3) is located between the sealing labyrinth disc (4) and the rear shaft neck (2), and a plurality of high-pressure turbine blades (5) are arranged on the high-pressure turbine disc (3); the method for detecting the outer diameter of the turbine rotor blade comprises the following steps:
the method comprises the following steps: the taper bolt (6) and the sealing labyrinth disc (4) are dismounted from the turbine rotor;
step two: one end of the jacking component is plugged into a gap between the bottom of a tenon of the high-pressure turbine blade (5) and a mortise of the high-pressure turbine disc (3);
step three: the mounting disc (7) is mounted on the high-pressure turbine disc (3) through the taper bolt (6), and a force application assembly is arranged on the mounting disc (7) at a position corresponding to the jacking assembly;
step four: a force along the axial direction of the turbine shaft (1) is applied to the jacking assembly through the force application assembly, the axial force is converted into a radial force through the jacking assembly, and the tenon of the high-pressure turbine blade (5) is tightly jacked with the mortise of the high-pressure turbine disc (3) without clearance;
step five: detecting the outer diameter of the high-pressure turbine blade (5), and judging whether the gap between the high-pressure turbine blade (5) and the casing is qualified;
the whole jacking assembly is of a T-shaped structure;
the jacking assembly comprises an inclined wedge block A (8) and an inclined wedge block B (9), the inclined wedge block A (8) is in contact with the high-pressure turbine disc (3), the inclined wedge block B (9) is in contact with the high-pressure turbine blade (5), the inclined wedge block B (9) and the inclined wedge block A (8) are mutually attached, and the upper parts of the attachment surfaces of the inclined wedge block A and the inclined wedge block B are inclined towards the direction far away from the turbine shaft (1);
the installation position of the force application component on the installation disc (7) corresponds to the inclined wedge block A (8);
the mounting position of the mounting plate (7) is the same as that of the sealing labyrinth plate (4), and the mounting plate plays a role in simulating the sealing labyrinth plate (4).
2. The method of sensing an outer diameter of a turbine rotor blade according to claim 1, wherein: an included angle between the jacking assembly and the axis of the turbine shaft (1) is an acute angle.
3. The method of sensing an outer diameter of a turbine rotor blade according to claim 1, wherein: one surface of the inclined wedge block A (8) far away from the inclined wedge block B (9) is an arc surface, and the arc surface partially extends into a gap between the bottom of the tenon of the high-pressure turbine blade (5) and the mortise of the high-pressure turbine disc (3).
4. The method of sensing an outer diameter of a turbine rotor blade according to claim 1, wherein: the force application assembly is in threaded connection with the mounting disc (7).
5. The method of sensing an outer diameter of a turbine rotor blade according to claim 4, wherein: the force application component is a screw (10), and the axis of the screw (10) is parallel to the axis of the turbine shaft (1).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010989799.7A CN111895951B (en) | 2020-09-18 | 2020-09-18 | Method for detecting outer diameter of turbine rotor blade |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010989799.7A CN111895951B (en) | 2020-09-18 | 2020-09-18 | Method for detecting outer diameter of turbine rotor blade |
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| CN111895951A CN111895951A (en) | 2020-11-06 |
| CN111895951B true CN111895951B (en) | 2022-09-30 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114505803A (en) * | 2020-11-16 | 2022-05-17 | 中国航发商用航空发动机有限责任公司 | Comb fluted disc assembly fixture |
| CN113701697B (en) * | 2021-07-06 | 2023-09-26 | 中国航发贵州黎阳航空动力有限公司 | Disk part circumferential tongue-and-groove detection method based on three coordinates |
| 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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| CN102128135A (en) * | 2010-01-18 | 2011-07-20 | 许开鴻 | Stroke-type air power energy generating equipment |
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| DE102006012009A1 (en) * | 2006-03-14 | 2007-09-20 | Robert Bosch Gmbh | Position measuring device for rotor blade adjusting device of wind turbine, has speed sensor provided for measuring relative rotation between piston rod and pitch angle adjusting unit or between pivot pin of cylinder and cylinder bearing |
| EP2647835B1 (en) * | 2012-04-04 | 2016-11-16 | Siemens Aktiengesellschaft | Flexible flap arrangement for a wind turbine rotor blade |
| CN202856473U (en) * | 2012-07-20 | 2013-04-03 | 林贵生 | Stepless convertible torque and speed adjustable direct drive electromotor or generator |
| JP6239491B2 (en) * | 2014-12-09 | 2017-11-29 | 三菱重工業株式会社 | Rotating machine state monitoring device, rotating machine, and rotating machine state monitoring method |
| US9869198B2 (en) * | 2015-05-13 | 2018-01-16 | General Electric Company | Intershaft integrated seal and lock-nut |
| CN108050913B (en) * | 2017-12-14 | 2020-04-14 | 中国航发沈阳发动机研究所 | Measuring device for outer diameter of turbine rotor |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101709691A (en) * | 2009-10-26 | 2010-05-19 | 陈国宝 | Ventilation and power generation dual-purpose constant speed wind generator |
| CN102128135A (en) * | 2010-01-18 | 2011-07-20 | 许开鴻 | Stroke-type air power energy generating equipment |
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