CN108168491A - A kind of erecting device for being used to measure turbine blade-tip gap sensor - Google Patents
A kind of erecting device for being used to measure turbine blade-tip gap sensor Download PDFInfo
- Publication number
- CN108168491A CN108168491A CN201711341273.2A CN201711341273A CN108168491A CN 108168491 A CN108168491 A CN 108168491A CN 201711341273 A CN201711341273 A CN 201711341273A CN 108168491 A CN108168491 A CN 108168491A
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- China
- Prior art keywords
- mounting base
- sensor
- interior
- convex platform
- neck bush
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Classifications
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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
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Control Of Turbines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a kind of for measuring the erecting device of turbine blade-tip gap sensor, belong to turbine blade-tip gap field of measuring technique.High-temperature turbine casing close to leaf position is provided with adjusting pad, and inner convex platform is welded on side of the high-temperature turbine casing far from blade tip, and interior mounting base is by being threadably mounted in inner convex platform；Outer lug boss is welded on the outside of combustion box, and outer mounting base upper end is overlapped on by its flange in outer lug boss, is provided with gasket between the two；The lower end of outer mounting base is connect with interior mounting base, and interior mounting base can be driven to rotate, and interior mounting base is screwed in inner convex platform；The test lead of sensor is provided with stop flange, and stop flange is pressed on adjusting pad, neck bush is provided between stop flange and interior mounting base and passes through neck bush compresses stop flange；On the cover board, cover board is mounted in outer lug boss for one end clamping installation of the sensor far from test lead.The present invention improves the accuracy and reliability of test and the reliability of locking.
Description
Technical field
The invention belongs to turbine blade-tip gap field of measuring technique, and in particular to one kind passes for measuring turbine blade-tip gap
The erecting device of sensor.
Background technology
High-pressure turbine tip clearance refer to High Pressure Turbine Rotor blade tip end face and high-pressure turbine stator casing inner wall it
Between distance, be engine design in an important parameter, have a great impact to the performance and safety of engine.
Tip clearance cross conference engine efficiency is caused to reduce, oil consumption rate raising, gap is too small, can lead to turn stator to touch mill, shadow
Ring the operational security of engine.Therefore, in engine design and experimental study, determine that tip clearance value as accurate as possible is shown
It obtains particularly important.At present, the method that tip clearance measures mainly has：Discharge probe measurement, capacitance measurement, electric eddy current measurement
Method and microwave measuring method etc., wherein capacitance measurement are because of its high sensitivity, probe temperature resistant capability is strong, the advantages such as small, wide
During the general tip clearance applied to each component of engine measures.The sensor that capacitance method uses is divided into large and small two by structure size
Kind model, large scale sensor are suitable for structure space at high-pressure turbine casing and constrain not strong, the less complicated feelings of assembly relation
Condition；Small size sensor then in the structure of compact in design advantageously.The high-pressure turbine blade tip that the country being currently known uses
Clearance measurement is large scale type with sensor, and small size type then has no use, the knot of installation sensor to match therewith
Structure device also there is no visible organization plan.
Invention content
Present disclosure：To solve the above-mentioned problems, the present invention proposes one kind for measuring turbine blade-tip gap biography
The erecting device of sensor measures difficult ask for solving the tip clearance of limited, compact in design the high-pressure turbine of structure space
Topic.
Technical scheme of the present invention：A kind of erecting device for being used to measure turbine blade-tip gap sensor, including：Adjustment
Pad, neck bush, interior mounting base, inner convex platform, outer mounting base and outer lug boss；
High-temperature turbine casing close to leaf position is provided with adjusting pad, and it is remote that the inner convex platform is welded on high-temperature turbine casing
Side from blade tip, the interior mounting base is by being threadably mounted in inner convex platform；
The outer lug boss is welded on the outside of combustion box, and the outer mounting base upper end is overlapped on institute by its flange
It states in outer lug boss, is provided with gasket between the two；
The lower end of the outer mounting base is connect with the interior mounting base, and interior mounting base can be driven to rotate, by interior installation
Seat is screwed in inner convex platform；
The test lead of sensor is provided with stop flange, and the stop flange is pressed on the adjusting pad, the limiting method
It is blue neck bush is provided between interior mounting base and passes through neck bush compress stop flange；
On the cover board, the cover board is mounted in outer lug boss for one end clamping installation of the sensor far from test lead.
Preferably, the interior mounting base is a cylinder；
Its one end close to outer mounting base four uniformly distributed mounting grooves such as is circumferentially provided with along it, the mounting groove with it is described
The locking boss cooperation of outer mounting base；
Threaded mounting portion is provided in the middle part of the interior mounting base, the threaded mounting portion coordinates with the inner convex platform；
The interior mounting base is provided with neck bush mounting hole close to one end of blade tip, and aperture is more than the interior mounting base
Internal diameter.
Preferably, the neck bush is fitted to using transition in the neck bush mounting hole, described neck bush one end
Compress the stop flange.
Preferably, the neck bush is divided into left and right two parts using a point half formula design along center.
Preferably, the cover board is divided into left and right two parts along center, whole rectangular；
Four corners are provided with bolt mounting holes, and center position two sides are respectively arranged with boss, and described one
Side boss is installed in the endoporus of the outer mounting base；
The boss is provided with centre bore, for clamping the sensor.
Preferably, the adjusting pad is pre-installed on the high-temperature turbine casing, and the adjusting pad is bonded in the biography
The test lead of sensor；
The bottom surface of the adjusting pad is concordant with the high-temperature turbine casing holding, by adjusting the thickness of adjusting pad, adjusts
Save distance between the test lead and blade of the sensor.
The advantageous effect of technical solution of the present invention：The present invention ensures to connect sensor test lead again not needing to block
In the case of installed, improve the accuracy and reliability of test；Using the connection of boss and groove between its inside and outside mounting base
Mode increases locking contact area, improves the reliability of locking.
Description of the drawings
Fig. 1 is that the present invention shows for measuring the installation of a preferred embodiment of the erecting device of turbine blade-tip gap sensor
It is intended to；
Fig. 2 is the sensor structure schematic diagram of embodiment illustrated in fig. 1；
Fig. 3 is the interior mounting base structure diagram of embodiment illustrated in fig. 1；
Fig. 4 is the outer mounting base structure diagram of embodiment illustrated in fig. 1；
Fig. 5 is the covering plate structure schematic diagram of embodiment illustrated in fig. 1；
Fig. 6 is the mounting groove schematic diagram of the interior mounting base of embodiment illustrated in fig. 1；
Fig. 7 is the locking boss schematic diagram of the outer mounting base of embodiment illustrated in fig. 1；
Wherein, 1- blades, 2- adjusting pads, 3- neck bush, mounting base in 4-, 5- sensors, 6- inner convex platforms, 7- high-temperature turbines
Casing, the outer mounting bases of 8-, 9- combustion boxes, 10- outer lug boss, 11- gaskets, 12- fastening bolts, 13- cover boards, 14- flanges
Side, 15- mounting grooves, 16- threaded mounting portions, 17- neck bush mounting holes, the locking boss of 18-, 19- stop flanges, 20- thunders illiteracy connect
Head.
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention with reference to attached drawing.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instructions such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on attached drawing institutes
The orientation or position relationship shown is for only for ease of the description present invention and simplifies description rather than instruction or imply signified dress
It puts or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of range.
As shown in Figures 1 to 7, it is a kind of for measuring the erecting device of turbine blade-tip gap sensor, including：Adjusting pad 2,
Neck bush 3, interior mounting base 4, inner convex platform 6, outer mounting base 8 and outer lug boss 10；
High-temperature turbine casing 7 close to 1 position of blade is prefabricated with for the mounting hole of mounting and adjusting pad 2, is selected suitable thick
The adjusting pad 2 of degree is installed in this hole；
Inner convex platform 6 is welded on side of the high-temperature turbine casing 7 far from blade tip, and interior mounting base 4 is by being threadably mounted at convex
In platform 6；
Outer lug boss 10 is welded on the outside of combustion box 9, and outer 8 upper end of mounting base is overlapped on evagination by its flange 14
On platform 10, and pass through fastening bolt 12 and be fixed in outer lug boss 10, outer mounting base 8 is provided with sealing between the two with outer lug boss 10
Pad 11, for being sealed to the cavity of combustion box 9.
The lower end of outer mounting base 8 is connected, and can drive interior installation with interior mounting base 4 using notch with boss mode
Seat 4 rotates, and interior mounting base 4 is screwed in inner convex platform 6, realizes the adjustment installation of internal mounting base 4 and adjusts neck bush 3 and limiting
Degree is compressed between flange 19, and then completes the fixation of the test lead of sensor 5, prevents its double swerve.
The test lead of sensor 5 is provided with stop flange 19, and sensor 5 is pressed in by stop flange 19 on adjusting pad 2, limit
Neck bush 3, which is provided with, between position flange 19 and interior mounting base 4 and passes through neck bush 3 compresses stop flange 19.
One end clamping of the sensor 5 far from test lead is mounted on cover board 13, and cover board 13 is mounted in outer lug boss 10.
In the present embodiment, interior mounting base 4 is a cylinder, be circumferentially provided with close to one end of outer mounting base 8 along it wait it is equal
Four mounting grooves 15 of cloth, mounting groove 15 and the locking boss 18 of outer 8 lower end of mounting base coordinate, and interior 4 middle part of mounting base is provided with
Threaded mounting portion 16 is mounted on by threaded mounting portion 16 on inner convex platform 6, and interior mounting base 4 is provided with interior close to one end of blade tip
Bushing mounting holes 17, aperture are more than the internal diameter of interior mounting base 4.
The locking boss 18 of outer mounting base 8 is inserted into being symmetrically installed in slot 15 of interior mounting base, rotate outer mounting base 8 make it is interior
Mounting base 4 is mounted in inner convex platform 6 by threaded mounting portion 16 and can prevent the loosening of interior mounting base 8.
In the present embodiment, neck bush 3 is fitted to using transition in neck bush mounting hole 17, and 3 one end of neck bush compresses
Stop flange 19 adjusts the installation axle of neck bush and stop flange 19 away from and then compression stop flange by rotating outer mounting base 8
19。
In the present embodiment, neck bush 3 is divided into left and right two parts along center, is facilitated the peace of neck bush 3 using a point half formula design
Dress also ensures the abundant compression to stop flange 19.
In the present embodiment, cover board 13 is divided into left and right two parts along center, whole rectangular；Four corners are provided with bolt
Mounting hole is mounted on by fastening bolt 12 in outer lug boss 10, and center position two sides are respectively arranged with boss, and side is convex
Platform is installed in the endoporus of outer mounting base 8, and device boss is provided with centre bore, and for clamping sensor 5, cover board 13 can be carried out
Effective limiting, clamps sensor 5 more firm.
In the present embodiment, adjusting pad 2 is pre-installed on high-temperature turbine casing 7, and adjusting pad 2 is bonded in the survey of sensor 5
End is tried, the bottom surface of adjusting pad 2 keeps concordant with high-temperature turbine casing 7, by adjusting the thickness of adjusting pad 2, adjusts sensor 5
Test lead and blade 1 between distance.
When sensor 5 is installed, inner convex platform 6 and outer lug boss 10 are welded to high whirlpool casing 7 and combustion box 9 first
On, adjusting pad 2 is then installed to the test lead of sensor 5 by the way of being glued, then by the lead of sensor 5 from interior installation
Seat 4 is pierced by, and is screwed in interior mounting base 4 in inner convex platform 6, and locked using outer mounting base 8.Load onto successively again gasket 11,
Cover board 13 is finally locked with bolt 12.
In this implementation, a diameter of φ 10 of its stop flange 19 of the test lead of sensor 5, other end thunder covers connector 20
A diameter of φ 9；
The effect of interior mounting base 4 is to compress the stop flange 19 of sensor head, prevents the radially vibration of sensor 5,
But the endoporus of interior mounting base 4 should be caused both to have can guarantee that the thunder across a diameter of φ 9 covered connector 20 when sensor 5 are installed,
Ensure to compress the stop flange on the head of a diameter of φ 10 again, therefore present invention employs interior mounting base 4 installation neck bush 3
Fixed solution, neck bush 3 to opening structure, covers after connector 20 passes through interior mounting base 4 in thunder using two halves, neck bush 3 installed
Onto interior mounting base 4, stop flange 19 is compressed using the lower face of neck bush 3；
In addition ensure that outer 8 endoporus of mounting base is more than the outer diameter that thunder covers connector 20, the use two halves of cover board 13 to opening structure by its
It clamps；The above organization plan ensure that be connect again after not needing to block its test lead during installing sensor 5
It is logical, it ensure that the reliability that sensor 5 connects.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Pipe is with reference to the foregoing embodiments described in detail the present invention, it will be understood by those of ordinary skill in the art that：It is still
It can modify to the technical solution recorded in foregoing embodiments or which part technical characteristic is equally replaced
It changes；And these modifications or replacement, the essence for various embodiments of the present invention technical solution that it does not separate the essence of the corresponding technical solution
God and range.
Claims (6)
1. a kind of erecting device for being used to measure turbine blade-tip gap sensor, which is characterized in that including：Adjusting pad (2), liner
Cover (3), interior mounting base (4), inner convex platform (6), outer mounting base (8) and outer lug boss (10)；
High-temperature turbine casing (7) close to blade (1) position is provided with adjusting pad (2), and the inner convex platform (6) is welded on high temperature whirlpool
Side of the casing (7) far from blade tip is taken turns, the interior mounting base (4) is by being threadably mounted in inner convex platform (6)；
The outer lug boss (10) is welded on the outside of combustion box (9), and outer mounting base (8) upper end passes through its flange
(14) it is overlapped in the outer lug boss (10), is provided with gasket (11) between the two；
The lower end of the outer mounting base (8) is connect with the interior mounting base (4), and interior mounting base (4) can be driven to rotate, by
Mounting base (4) is screwed in inner convex platform (6)；
The test lead of sensor (5) is provided with stop flange (19), and the stop flange (19) is pressed on the adjusting pad (2),
Neck bush (3) is provided between the stop flange (19) and interior mounting base (4) and passes through neck bush (3) and compresses stop flange
(19)；
One end clamping of the sensor (5) far from test lead is mounted on cover board (13), and the cover board (13) is mounted on evagination
On platform (10).
2. the erecting device as described in claim 1 for being used to measure turbine blade-tip gap sensor, it is characterised in that：In described
Mounting base (4) is a cylinder；
Its one end close to outer mounting base (8) four uniformly distributed mounting grooves (15), the mounting groove such as is circumferentially provided with along it
(15) coordinate with the locking boss (18) of outer mounting base (8) lower end；
Threaded mounting portion (16) is provided in the middle part of the interior mounting base (4), by the threaded mounting portion (16) mounted on described
On inner convex platform (6)；
The interior mounting base (4) is provided with neck bush mounting hole (17) close to one end of blade tip, and aperture is more than the interior installation
The internal diameter of seat (4).
3. the erecting device as claimed in claim 2 for being used to measure turbine blade-tip gap sensor, it is characterised in that：In described
Bushing (3) is fitted to using transition in the neck bush mounting hole (17), and described neck bush (3) one end compresses the limiting
Flange (19).
4. the erecting device as described in claim 1 for being used to measure turbine blade-tip gap sensor, it is characterised in that：In described
Bushing (3) is divided into left and right two parts using a point half formula design along center.
5. the erecting device as described in claim 1 for being used to measure turbine blade-tip gap sensor, it is characterised in that：The lid
Plate (13) is divided into left and right two parts along center, whole rectangular；
Four corners are provided with bolt mounting holes, and center position two sides are respectively arranged with boss, and the side is convex
Platform is installed in the endoporus of the outer mounting base (8)；
The boss is provided with centre bore, for clamping the sensor (5).
6. the erecting device as described in claim 1 for being used to measure turbine blade-tip gap sensor, it is characterised in that：The tune
Whole pad (2) is pre-installed on the high-temperature turbine casing (7), and the adjusting pad (2) is bonded in the test of the sensor (5)
End；
The bottom surface of the adjusting pad (2) is concordant with high-temperature turbine casing (7) holding, by the thickness for adjusting adjusting pad (2)
Degree, adjusts distance between the test lead of the sensor (5) and blade (1).
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 |
Applications Claiming Priority (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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108168491A true CN108168491A (en) | 2018-06-15 |
| CN108168491B CN108168491B (en) | 2020-04-21 |
Family
ID=62525477
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711341273.2A Active CN108168491B (en) | 2017-12-14 | 2017-12-14 | A installation device for measuring turbine apex clearance sensor |
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| Country | Link |
|---|---|
| CN (1) | CN108168491B (en) |
Cited By (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 |
| CN113959391A (en) * | 2021-09-27 | 2022-01-21 | 中国航发沈阳发动机研究所 | Internal parameter measuring structure of double-layer casing of engine |
| CN114294068A (en) * | 2021-10-20 | 2022-04-08 | 中国航发四川燃气涡轮研究院 | Mounting structure and turbine engine of apex clearance sensor on double-deck quick-witted casket |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103133060A (en) * | 2011-11-25 | 2013-06-05 | 中航商用航空发动机有限责任公司 | Method for controlling gap between blade tip of turbine casing and blade tip of turbine 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 |
-
2017
- 2017-12-14 CN CN201711341273.2A patent/CN108168491B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103133060A (en) * | 2011-11-25 | 2013-06-05 | 中航商用航空发动机有限责任公司 | Method for controlling gap between blade tip of turbine casing and blade tip of turbine 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 |
Cited By (4)
| 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 |
| CN113959391A (en) * | 2021-09-27 | 2022-01-21 | 中国航发沈阳发动机研究所 | Internal parameter measuring structure of double-layer casing of engine |
| 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 |
| CN114294068A (en) * | 2021-10-20 | 2022-04-08 | 中国航发四川燃气涡轮研究院 | Mounting structure and turbine engine of apex clearance sensor on double-deck quick-witted casket |
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| Publication number | Publication date |
|---|---|
| CN108168491B (en) | 2020-04-21 |
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