CN108168491B - A installation device for measuring turbine apex clearance sensor - Google Patents
A installation device for measuring turbine apex clearance sensor Download PDFInfo
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- CN108168491B CN108168491B CN201711341273.2A CN201711341273A CN108168491B CN 108168491 B CN108168491 B CN 108168491B CN 201711341273 A CN201711341273 A CN 201711341273A CN 108168491 B CN108168491 B CN 108168491B
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- mounting seat
- boss
- mounting
- sensor
- blade tip
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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
- G01B21/16—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 distance of clearance between spaced objects
Abstract
The invention discloses a mounting device for a sensor for measuring turbine blade tip clearance, and belongs to the technical field of turbine blade tip clearance measurement. The high-temperature turbine casing close to the blade is provided with an adjusting pad, the inner boss is welded on one side of the high-temperature turbine casing far away from the blade tip, and the inner mounting seat is mounted in the inner boss through threads; the outer boss is welded on the outer side of the combustion chamber casing, the upper end of the outer mounting seat is in lap joint with the outer boss through a flange edge of the outer mounting seat, and a sealing gasket is arranged between the outer boss and the outer boss; the lower end of the outer mounting seat is connected with the inner mounting seat and can drive the inner mounting seat to rotate so as to screw the inner mounting seat into the inner boss; a limit flange is arranged at the testing end of the sensor and pressed on the adjusting pad, and an inner bushing is arranged between the limit flange and the inner mounting seat and tightly presses the limit flange through the inner bushing; the end of the sensor far away from the testing end is clamped and installed on a cover plate, and the cover plate is installed on an outer boss. The invention improves the accuracy and reliability of the test and the reliability of locking.
Description
Technical Field
The invention belongs to the technical field of turbine blade tip clearance measurement, and particularly relates to a mounting device for a sensor for measuring turbine blade tip clearance.
Background
The high-pressure turbine blade tip clearance refers to the distance between the blade tip surface of a high-pressure turbine rotor blade and the inner wall of a high-pressure turbine stator casing, is an important technical parameter in the design of an engine, and has great influence on the performance and the safety of the engine. The excessive clearance of the blade tip can cause the efficiency reduction and the oil consumption rate increase of the engine, and the excessive clearance can cause the collision and abrasion of the rotor and the stator, thereby influencing the running safety of the engine. Therefore, it is important to determine the blade tip clearance value as accurately as possible in engine design and experimental research. At present, the method for measuring the blade tip clearance mainly comprises the following steps: the method comprises the following steps of measuring a discharge probe, a capacitance, an eddy current and a microwave, wherein the capacitance is widely applied to measuring the tip clearance of each part of the engine due to the advantages of high sensitivity, strong temperature resistance of a probe, small size and the like. The sensors used by the capacitance method are divided into a large type and a small type according to the structural size, and the large-size sensor is suitable for the conditions that the structural space at the high-pressure turbine casing is not strongly restricted and the assembly relation is not complex; the small size of the sensor is more advantageous in a compact layout configuration. At present, the known domestic sensors for measuring the blade tip clearance of the high-pressure turbine are large-size sensors, the small-size sensors are not used, and a matched structural device for mounting the sensors has no visible structural scheme.
Disclosure of Invention
The invention comprises the following contents: in order to solve the problems, the invention provides a mounting device for a sensor for measuring the turbine blade tip clearance, which is used for solving the problem that the blade tip clearance of a high-pressure turbine with limited structural space and compact layout is difficult to measure.
The technical scheme of the invention is as follows: a mounting device for a turbine tip clearance sensor, comprising: the adjusting device comprises an adjusting pad, an inner bushing, an inner mounting seat, an inner boss, an outer mounting seat and an outer boss;
the high-temperature turbine casing close to the blades is provided with an adjusting pad, the inner boss is welded on one side of the high-temperature turbine casing far away from the blade tips, and the inner mounting seat is mounted in the inner boss through threads;
the outer boss is welded on the outer side of the combustion chamber casing, the upper end of the outer mounting seat is in lap joint with the outer boss through a flange edge of the outer mounting seat, and a sealing gasket is arranged between the outer boss and the outer boss;
the lower end of the outer mounting seat is connected with the inner mounting seat and can drive the inner mounting seat to rotate so as to screw the inner mounting seat into the inner boss;
a limit flange is arranged at the testing end of the sensor and pressed on the adjusting pad, and an inner bushing is arranged between the limit flange and the inner mounting seat and tightly presses the limit flange through the inner bushing;
the sensor is far away from the one end centre gripping of test end and is installed on the apron, the apron is installed on outer boss.
Preferably, the inner mounting seat is a cylinder;
four mounting grooves which are uniformly distributed are formed in one end, close to the outer mounting seat, of the mounting groove along the circumferential direction of the mounting groove, and the mounting grooves are matched with the anti-loosening bosses of the outer mounting seat;
the middle part of the inner mounting seat is provided with a threaded mounting part which is matched with the inner boss;
and one end of the inner mounting seat, which is close to the blade tip, is provided with an inner bushing mounting hole, and the aperture of the inner bushing mounting hole is larger than the inner diameter of the inner mounting seat.
Preferably, the inner bushing is installed in the inner bushing installation hole in a transition fit mode, and one end of the inner bushing compresses the limiting flange.
Preferably, the inner lining is designed in a half-split mode and is divided into a left part and a right part along the center.
Preferably, the cover plate is divided into a left part and a right part along the center, and the whole cover plate is rectangular;
bolt mounting holes are formed in four corners of the cover plate (13), bosses are arranged on two side faces of the center of the cover plate respectively, and the bosses on one side are mounted in inner holes of the outer mounting seats;
the boss is provided with a center hole for clamping the sensor.
Preferably, the adjusting pad is pre-installed on the high-temperature turbine casing, and the adjusting pad is bonded to the testing end of the sensor;
the lower bottom surface of the adjusting pad is flush with the high-temperature turbine casing, and the distance between the testing end of the sensor and the blade is adjusted by adjusting the thickness of the adjusting pad.
The technical scheme of the invention has the beneficial effects that: the invention ensures that the installation is carried out under the condition that the test lead of the sensor is not required to be cut off and then connected, thereby improving the accuracy and reliability of the test; the connection mode of the boss and the groove is adopted between the inner mounting seat and the outer mounting seat, the anti-loosening contact area is increased, and the locking reliability is improved.
Drawings
FIG. 1 is a schematic view of a preferred embodiment of the mounting apparatus for a turbine tip clearance sensor of the present invention;
FIG. 2 is a schematic diagram of a sensor configuration of the embodiment shown in FIG. 1;
FIG. 3 is a schematic view of the inner mount structure of the embodiment shown in FIG. 1;
FIG. 4 is a schematic view of the outer mount structure of the embodiment shown in FIG. 1;
FIG. 5 is a schematic view of the cover plate structure of the embodiment shown in FIG. 1;
FIG. 6 is a schematic view of a mounting slot of the inner mount of the embodiment shown in FIG. 1;
FIG. 7 is a schematic view of a locking boss of the outer mount of the embodiment shown in FIG. 1;
the turbine engine comprises a blade 1, a blade 2, an adjusting pad 3, an inner bushing 4, an inner mounting seat 5, a sensor 6, an inner boss 7, a high-temperature turbine case 8, an outer mounting seat 9, a combustion chamber case 10, an outer boss 11, a sealing pad 12, a fastening bolt 13, a cover plate 14, a flange edge 14, a mounting groove 15, a threaded mounting part 16, an inner bushing mounting hole 17, an anti-loosening boss 18, a limiting flange 19 and a Raymond joint 20.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
As shown in fig. 1 to 7, a mounting device for a turbine tip clearance sensor includes: the adjustable sleeve comprises an adjusting pad 2, an inner bushing 3, an inner mounting seat 4, an inner boss 6, an outer mounting seat 8 and an outer boss 10;
a mounting hole for mounting the adjusting pad 2 is prefabricated in the high-temperature turbine casing 7 close to the blade 1, and the adjusting pad 2 with proper thickness is selected to be mounted in the mounting hole;
the inner boss 6 is welded on one side of the high-temperature turbine casing 7 far away from the blade tip, and the inner mounting seat 4 is mounted in the inner boss 6 through threads;
the outer boss 10 is welded on the outer side of the combustion chamber casing 9, the upper end of the outer mounting seat 8 is lapped on the outer boss 10 through a flange edge 14 of the outer mounting seat and is fixed on the outer boss 10 through a fastening bolt 12, and a sealing gasket 11 is arranged between the outer mounting seat 8 and the outer boss 10 and used for sealing a cavity of the combustion chamber casing 9.
The lower extreme of outer mount pad 8 adopts notch and boss mode cooperation to be connected with interior mount pad 4 to can drive interior mount pad 4 rotatory, with interior mount pad 4 screw in boss 6, realize compressing tightly the degree between adjustment installation and the adjustment neck bush 3 of interior mount pad 4 and the spacing flange 19, and then accomplish the fixed of sensor 5's test end, prevent to rock about it.
The testing end of the sensor 5 is provided with a limiting flange 19, the sensor 5 is pressed on the adjusting pad 2 through the limiting flange 19, an inner bushing 3 is arranged between the limiting flange 19 and the inner mounting seat 4, and the limiting flange 19 is pressed through the inner bushing 3.
The end of the sensor 5 far away from the testing end is clamped and installed on a cover plate 13, and the cover plate 13 is installed on the outer boss 10.
In this embodiment, interior mount pad 4 is a barrel, and its one end that is close to outer mount pad 8 is provided with four mounting grooves 15 of equipartition such as along its circumference, and mounting groove 15 cooperates with locking boss 18 of outer mount pad 8 lower extreme, and interior mount pad 4 middle part is provided with screw thread installation department 16, installs on interior boss 6 through screw thread installation department 16, and the one end that interior mount pad 4 is close to the apex is provided with interior bush mounting hole 17, and its aperture is greater than the internal diameter of interior mount pad 4.
The anti-loosening boss 18 of the outer mounting seat 8 is inserted into the symmetrical mounting groove 15 of the inner mounting seat, and the outer mounting seat 8 is rotated to enable the inner mounting seat 4 to be mounted in the inner boss 6 through the threaded mounting part 16 and prevent the inner mounting seat 8 from loosening.
In this embodiment, the inner bushing 3 is installed in the inner bushing installation hole 17 in a transition fit manner, one end of the inner bushing 3 compresses the limiting flange 19, and the outer installation base 8 is rotated to adjust the installation wheelbase of the inner bushing and the limiting flange 19, so as to compress the limiting flange 19.
In this embodiment, the inner bushing 3 is designed in a half-split manner, and is divided into a left part and a right part along the center, so that the inner bushing 3 can be conveniently installed, and the limit flange 19 can be fully compressed.
In this embodiment, the cover plate 13 is divided into a left part and a right part along the center, and the whole is rectangular; the four corners of apron 13 are provided with the bolt mounting hole, install on outer boss 10 through fastening bolt 12, and its central point department both sides face is provided with the boss respectively, and one side boss is installed in the hole of outer mount pad 8, and the ware boss is provided with the centre bore for centre gripping sensor 5 can carry out effectual spacing to apron 13, makes sensor 5 centre gripping more firm.
In this embodiment, the adjustment pad 2 is pre-installed on the high-temperature turbine casing 7, the adjustment pad 2 is adhered to the testing end of the sensor 5, the lower bottom surface of the adjustment pad 2 is flush with the high-temperature turbine casing 7, and the distance between the testing end of the sensor 5 and the blade 1 is adjusted by adjusting the thickness of the adjustment pad 2.
When the sensor 5 is installed, firstly, the inner boss 6 and the outer boss 10 are respectively welded on the high-vortex case 7 and the combustion chamber case 9, then the adjusting pad 2 is installed at the testing end of the sensor 5 in a gluing mode, then the lead of the sensor 5 penetrates out of the inner installation seat 4, and the inner installation seat 4 is screwed into the inner boss 6 through the outer installation seat 8 and is locked. Then the sealing gasket 11 and the cover plate 13 are sequentially arranged, and finally the sealing gasket and the cover plate are locked by the bolt 12.
In the implementation, the diameter of the limiting flange 19 at the testing end of the sensor 5 is phi 10, and the diameter of the Raymond joint 20 at the other end of the sensor is phi 9;
the inner mounting seat 4 is used for pressing a limiting flange 19 at the head of the sensor to prevent the sensor 5 from moving along the radial direction, but when the sensor 5 is mounted, an inner hole of the inner mounting seat 4 can ensure that the inner hole can penetrate through a Raymond joint 20 with the diameter of phi 9 and can also ensure that the limiting flange at the head with the diameter of phi 10 is pressed tightly, so that the fixing scheme that the inner mounting seat 4 is additionally provided with the inner lining 3 is adopted, the inner lining 3 adopts a two-half split structure, after the Raymond joint 20 penetrates through the inner mounting seat 4, the inner lining 3 is mounted on the inner mounting seat 4, and the lower end face of the inner lining 3 is used for pressing the limiting flange 19;
in addition, the inner hole of the outer mounting seat 8 is ensured to be larger than the outer diameter of the Raymond joint 20, and the cover plate 13 is clamped by adopting a two-half split structure; the structural schemes ensure that the test lead of the sensor 5 is not required to be connected after being cut off in the process of mounting the sensor 5, and ensure the connection reliability of the sensor 5.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (6)
1. A mounting device for a turbine blade tip clearance sensor, comprising: the adjustable bushing comprises an adjusting pad (2), an inner bushing (3), an inner mounting seat (4), an inner boss (6), an outer mounting seat (8) and an outer boss (10);
the high-temperature turbine casing (7) close to the position of the blade (1) is provided with an adjusting pad (2), the inner boss (6) is welded on one side, far away from the blade tip, of the high-temperature turbine casing (7), and the inner mounting seat (4) is mounted in the inner boss (6) through threads;
the outer boss (10) is welded on the outer side of the combustion chamber casing (9), the upper end of the outer mounting seat (8) is in lap joint with the outer boss (10) through a flange edge (14) of the outer mounting seat, and a sealing gasket (11) is arranged between the outer boss and the outer boss;
the lower end of the outer mounting seat (8) is connected with the inner mounting seat (4) and can drive the inner mounting seat (4) to rotate, and the inner mounting seat (4) is screwed into the inner boss (6);
a limit flange (19) is arranged at the testing end of the sensor (5), the limit flange (19) is pressed on the adjusting pad (2), an inner bushing (3) is arranged between the limit flange (19) and the inner mounting seat (4), and the limit flange (19) is pressed by the inner bushing (3);
one end, far away from the testing end, of the sensor (5) is clamped and installed on a cover plate (13), and the cover plate (13) is installed on an outer boss (10).
2. The mounting device for a turbine blade tip clearance sensor of claim 1, wherein: the inner mounting seat (4) is a cylinder;
four mounting grooves (15) which are uniformly distributed are formed in one end, close to the outer mounting seat (8), of the mounting groove along the circumferential direction of the mounting groove, and the mounting grooves (15) are matched with a locking boss (18) at the lower end of the outer mounting seat (8);
a thread mounting part (16) is arranged in the middle of the inner mounting seat (4) and is mounted on the inner boss (6) through the thread mounting part (16);
an inner bushing mounting hole (17) is formed in one end, close to the blade tip, of the inner mounting seat (4), and the aperture of the inner bushing mounting hole is larger than the inner diameter of the inner mounting seat (4).
3. The mounting device for a turbine blade tip clearance sensor of claim 2, wherein: the inner bushing (3) is installed in the inner bushing installation hole (17) in a transition fit mode, and one end of the inner bushing (3) compresses the limiting flange (19).
4. The mounting device for a turbine blade tip clearance sensor of claim 1, wherein: the inner bushing (3) is designed in a half-split mode and is divided into a left part and a right part along the center.
5. The mounting device for a turbine blade tip clearance sensor of claim 1, wherein: the cover plate (13) is divided into a left part and a right part along the center, and the whole body of the cover plate is rectangular;
bolt mounting holes are formed in four corners of the cover plate (13), bosses are arranged on two side faces of the center of the cover plate respectively, and the bosses on one side are mounted in inner holes of the outer mounting seats (8);
the boss is provided with a central hole for clamping the sensor (5).
6. The mounting device for a turbine blade tip clearance sensor of claim 1, wherein: the adjusting pad (2) is pre-installed on the high-temperature turbine casing (7), and the adjusting pad (2) is bonded to the testing end of the sensor (5);
the lower bottom surface of the adjusting pad (2) and the high-temperature turbine casing (7) are kept flush, and the distance between the testing end of the sensor (5) and the blade (1) is adjusted by adjusting the thickness of the adjusting pad (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711341273.2A CN108168491B (en) | 2017-12-14 | 2017-12-14 | A installation device for measuring turbine apex clearance sensor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711341273.2A CN108168491B (en) | 2017-12-14 | 2017-12-14 | A installation device for measuring turbine apex clearance sensor |
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| CN108168491A CN108168491A (en) | 2018-06-15 |
| CN108168491B true CN108168491B (en) | 2020-04-21 |
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| CN201711341273.2A Active CN108168491B (en) | 2017-12-14 | 2017-12-14 | A installation device for measuring turbine apex clearance sensor |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109870099A (en) * | 2019-03-15 | 2019-06-11 | 中国航发沈阳发动机研究所 | A kind of high temperature resisting rotor continuous surface radial clearance measuring system and method |
| CN113959391B (en) * | 2021-09-27 | 2024-03-22 | 中国航发沈阳发动机研究所 | Internal parameter measuring structure of double-layer casing of engine |
| CN114294068B (en) * | 2021-10-20 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Mounting structure of blade tip clearance sensor on double-layer casing and turbine engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103133060B (en) * | 2011-11-25 | 2015-10-21 | 中航商用航空发动机有限责任公司 | Gas turbine engine and control the method in gap between turbine casing and rotor blade |
| CN106643458A (en) * | 2017-01-19 | 2017-05-10 | 中国航发沈阳发动机研究所 | Capacitance-type blade tip gap testing sensor mounting device |
| CN106940177A (en) * | 2017-02-13 | 2017-07-11 | 中国航发沈阳发动机研究所 | A kind of turborotor half window throat area measuring method |
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