CN114152204A - Aero-engine blade tip clearance detection device - Google Patents
Aero-engine blade tip clearance detection device Download PDFInfo
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- CN114152204A CN114152204A CN202111350602.6A CN202111350602A CN114152204A CN 114152204 A CN114152204 A CN 114152204A CN 202111350602 A CN202111350602 A CN 202111350602A CN 114152204 A CN114152204 A CN 114152204A
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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
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/14—Measuring arrangements characterised by the use of optical techniques for measuring distance or clearance between spaced objects or spaced apertures
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Abstract
The embodiment of the application belongs to the technical field of detection equipment, and particularly relates to an aeroengine blade tip clearance detection device which is used for solving the technical problem that whether the distance between other positions of the inner wall of a casing along the circumferential direction and a blade meets the requirement or not so as to enable the detection reliability of the detection device to be low. It includes: the turbine rotor comprises a driving unit, a mounting unit and an image acquisition device, wherein the driving unit is in transmission connection with a rotor, the mounting unit is arranged at one end of the turbine rotor and comprises a first mounting frame, a first adapter shaft and a synchronous driving device, and the first adapter shaft is rotatably connected with the first mounting frame; the first mounting bracket is used for being connected with the casing, the synchronous driving device is in transmission connection with the first transfer shaft, the synchronous driving device is used for driving the first transfer shaft to rotate synchronously with the rotor, the image acquisition device is arranged on the first transfer shaft, the blade tip clearance in the circumferential direction of the blade can be acquired by rotating the image acquisition device for a circle, and the detection reliability of the detection device is further improved.
Description
Technical Field
The embodiment of the application belongs to the technical field of detection equipment, and particularly relates to a blade tip clearance detection device for an aero-engine.
Background
An aircraft engine is a power device of an aircraft, generally takes continuously flowing gas as a working medium, and converts heat energy into rotary mechanical energy to provide power for the flight of the aircraft. The aero-engine comprises a casing and a rotor arranged in the casing, the rotor comprises a gas compressor rotor and a turbine rotor, wherein a plurality of blades are arranged on the periphery of a blade disc of the turbine rotor, and when the aero-engine works, the working medium drives the blades of the turbine rotor to rotate so as to drive a rotating shaft to rotate, so that power is output.
In the related art, in order to ensure that the clearance between the blade tip of the turbine blade and the inner wall of the casing is within an allowable range, the clearance is generally detected by a detection device; specifically, detection device includes displacement sensor and mounting bracket, and displacement sensor sets up on the mounting bracket, is equipped with the trompil in the position that the casket corresponds the blade, sets up displacement sensor in trompil department through the mounting bracket, and displacement sensor is used for detecting every apex to its distance.
However, in the related art, only the distance between the inner wall of the casing corresponding to the opening and each blade can be detected, and the distances between the inner wall of the casing and the blades at other positions along the circumferential direction cannot be detected, so that the distances between the inner wall of the casing and each blade cannot be detected completely, and the detection reliability of the detection device is low.
Disclosure of Invention
The main purpose of the embodiment of the application is to provide an aeroengine blade tip clearance detection device, in order to solve the problem that whether the distance between the blade and other positions of the inner wall of the casing along the circumferential direction meets the requirements or not can not be confirmed, so as to influence the performance of the engine.
The application embodiment provides an aeroengine apex clearance detection device includes: a drive unit, a mounting unit, and an image acquisition device; the driving unit is used for being in transmission connection with the rotor and is used for driving the rotor to rotate in the casing; the mounting unit is used for being arranged at one end of the turbine rotor and comprises a first mounting frame, a first adapter shaft and a synchronous driving device, the first mounting frame is used for being fixedly connected with a casing, the first adapter shaft is rotatably connected with the first mounting frame, and the axis of the first adapter shaft and the axis of the rotor are arranged in a collinear manner; the synchronous driving device is connected with the first adapter shaft and is used for driving the first adapter shaft and the rotor to synchronously rotate; the image acquisition device is arranged on the first adapter shaft and used for acquiring images of the blade tips of the turbine blades and the inner wall of the casing so as to acquire the distance between the blade tips and the inner wall of the casing according to the images.
Further, aeroengine apex clearance detection device still includes the light source, the light source sets up on first switching axle, the light source is used for to the machine casket inner wall with emitting light between the blade.
Further, the light source includes a line structured light projector, the light rays generated by the line structured light projector are located in the same plane, and the axis of the rotor is located in the plane.
Further, the installation unit still includes the fixing base, the fixing base with first switching axle detachable connects, line structure light projector with image acquisition device all sets up on the fixing base.
Further, synchronous drive device includes a servo motor, a servo motor sets up on the first mounting bracket, a servo motor's main shaft with first switching shaft transmission is connected.
Further, the first mounting frame comprises a first fixing ring and a first hub positioned in the first fixing ring, and the first hub is fixedly connected with the first fixing ring; the first fixing ring is used for connecting the casing;
the first hub is provided with a first rotating hole, and the first rotating shaft is rotatably arranged in the rotating hole in a penetrating mode.
Further, the circumference of first solid fixed ring encircles and is equipped with a plurality of rings of evenly distributed.
Further, the first transfer shaft is rotatably arranged in a shaft hole of the rotor, and a supporting bearing matched with the shaft hole is arranged on the first transfer shaft.
Further, the driving unit is arranged at a rotor end of the compressor, and comprises a second servo motor, a second mounting frame and a second adapter shaft, the second mounting frame is connected with the casing, the second adapter shaft is rotatably connected with the second mounting frame, and the second adapter shaft is in transmission connection with the rotor; the second servo motor is installed on the second mounting rack, and a main shaft of the second servo motor is in transmission connection with the second adapter shaft.
Further, the second mounting bracket includes the solid fixed ring of second and is located second wheel hub in the solid fixed ring of second, the solid fixed ring of second be used for with the machine casket is connected, second wheel hub is last to be provided with the second and rotates the hole, the rotatable wearing and tearing of second switching shaft establish in the second rotates the hole, second servo motor with second wheel hub connects.
The application embodiment provides an aeroengine apex clearance detection device includes: the mounting unit comprises a first mounting frame, a first adapter shaft and a synchronous driving device, the first adapter shaft is rotatably connected with the first mounting frame, and the axis of the first adapter shaft and the axis of the rotor are arranged in a collinear manner; the first mounting bracket is used for being connected with the casing, the synchronous driving device is in transmission connection with the first transfer shaft, the synchronous driving device is used for driving the first transfer shaft to rotate synchronously with the rotor, the image acquisition device is arranged on the first transfer shaft and used for acquiring images of the blade tips of the turbine blades and the inner wall of the casing, the image acquisition device rotates for a circle to acquire blade tip gaps in the circumferential direction of the blades, and therefore the detection reliability of the detection device is improved.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments or related technologies of the present application, the drawings needed to be used in the description of the embodiments or related technologies are briefly introduced below, it is obvious that the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is an assembly schematic diagram of an aircraft engine blade tip clearance detection device provided by an embodiment of the application;
FIG. 2 is a cross-sectional view of a mounting unit of an aircraft engine inspection device provided in an embodiment of the present application;
FIG. 3 is an isometric view of a drive unit of an aircraft engine inspection device provided in an embodiment of the present application;
fig. 4 is a schematic structural diagram of a fixing seat of the aircraft engine detection device provided in the embodiment of the present application;
fig. 5 is a right side view of a mounting unit of an aircraft engine detection device provided in an embodiment of the present application.
Description of reference numerals:
10 a casing; 100-a rotor;
110-a turbine rotor; 120-compressor rotor;
131-front journal; 132-rear journal;
140-a blade; 150-a stationary vane;
20-a mounting unit; 210-a first mount;
211-a first retaining ring; 212-a first hub;
213-first connecting rod; 214-a lifting ring;
220-a first transfer shaft; 230-a first servo motor;
240-positioning cover; 241-positioning the shaft sleeve;
242-end cap; 243-mounting ring;
244 — a first bearing; 245-a first support ring;
250-a support bearing;
30-an image acquisition device; 310-a camera;
a 320-line structured light projector; 321-line structured light;
330-a fixed seat; 331-a mounting seat;
332-a support seat;
40-a drive unit; 410-a second servo motor;
420-a second mounting frame; 421-a second retaining ring;
422-a second hub; 423-second connecting rod;
424-a second support ring; 430-second transfer shaft.
With the above figures, there are shown specific embodiments of the present application, which will be described in more detail below. These drawings and written description are not intended to limit the scope of the inventive concepts in any manner, but rather to illustrate the inventive concepts to those skilled in the art by reference to specific embodiments.
Detailed Description
The rotor of the aircraft engine comprises a compressor rotor and a turbine rotor which are coaxial. The impeller is arranged on the compressor rotor and the turbine rotor and comprises an impeller disc and blades arranged on the periphery of the impeller disc, the top ends of the blades are blade tips, the distance between the blade tips and the inner wall of a casing is called blade tip clearance, the blade tip clearance is one of important parameters influencing the performance of an engine, in order to improve the performance and the efficiency of the engine, the blade tip clearance of the rotor is required to be as small as possible so as to reduce loss caused by leakage of working media, however, the clearance is too small, so that the blade tips and the casing are easy to rub and the safety of the engine is influenced, therefore, in the installation process, the blade tip clearance is determined to be within an allowable range, and the impeller is an important factor ensuring the performance of the aero-engine.
In the related art, generally, the blade tip clearance needs to be detected through a detection device, the detection device comprises a displacement sensor and a mounting frame, the displacement detection device is arranged on the mounting frame, an opening is formed in the position, corresponding to the blade, of the casing, the displacement sensor is arranged at the opening through the mounting frame, and the displacement detection device is used for detecting the distance from each blade tip to the displacement detection device.
However, due to insufficient machining precision, the roundness of the inner wall of the casing is not sufficient, or the casing is easily deflected due to the influence of mechanical load, and the tip clearance of the blade along the circumferential direction is greatly changed.
In view of this, the embodiment of the present application provides an aeroengine blade tip clearance detection device, including: the mounting unit comprises a first mounting frame, a first adapter shaft and a synchronous driving device, wherein the first adapter shaft is mounted on the first mounting frame in a rotating mode, the first adapter shaft is rotatably connected with the first mounting frame, the image acquisition device is mounted on the first adapter shaft, the first adapter shaft is driven by the synchronous driving device to rotate synchronously with the rotor, and blade tip gaps in the circumferential direction of the blade can be acquired by rotating the image acquisition device for one circle; that is to say, the image acquisition device can detect blade tip clearances at various positions of the inner wall of the casing and the blade to prevent the blade tip clearances between partial inner wall of the casing and the blade from exceeding an allowable range, thereby improving the detection reliability of the detection device.
The technical solutions in the embodiments of the present application will be described clearly and completely with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. 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 application.
Fig. 1 is an assembly schematic view of an aircraft engine blade tip clearance detection device provided in an embodiment of the present application, fig. 2 is a cross-sectional view of an installation unit of the aircraft engine detection device provided in the embodiment of the present application, fig. 3 is an axial side view of a drive unit of the aircraft engine detection device provided in the embodiment of the present application, fig. 4 is a structural schematic view of a fixing base of the aircraft engine detection device provided in the embodiment of the present application, and fig. 5 is a right side view of the installation unit of the aircraft engine detection device provided in the embodiment of the present application.
Referring to fig. 1, the aircraft engine mainly includes a casing 10, and a compressor, a combustor and a turbine located in the casing 10, the compressor is mainly responsible for sucking air from the surrounding atmosphere and pressurizing the air, the pressurized air is supplied to the combustion chamber for combustion, and the high-temperature and high-pressure gas combusted by the combustion chamber flows through the turbine and drives the turbine to rotate so as to output mechanical energy. The compressor comprises a compressor rotor 120, the turbine comprises a turbine rotor 110, the compressor rotor 120 and the turbine rotor 110 are coaxial, and the compressor rotor 120 and the turbine rotor 110 form a rotor 100 of the aircraft engine; the rotor 100 includes a rotating shaft, an impeller and blades 140, a bladed disc is mounted on the rotating shaft, a plurality of blades 140 are arranged on the periphery of the bladed disc, the bladed disc is multi-stage, the multi-stage bladed disc is arranged at intervals along the axis of the rotating shaft, the rotating shaft includes a front journal 131 (left end in fig. 1) located on the compressor rotor 120 and a rear journal 132 (right end in fig. 1) located on the turbine rotor 110, and a positioning bearing is arranged at the end of the front journal 131. Since the blades rotate along with the rotating shaft, the blades on the rotor are also called as movable blades, a stationary blade 150 for guiding flow is arranged on one side of each stage of blade disc of the turbine rotor 110 facing the front journal 131, the stationary blade 150 is mounted on the inner wall of the engine casing 10, and in order to prevent the stationary blade 150 from affecting the detection of the blade tip clearance, the blade tip clearance detection device of the aero engine in the embodiment can detect the blade tip clearance of the blade 140 of the turbine rotor 110 far away from the front journal 131.
With continued reference to fig. 1, the aeroengine blade tip clearance detection device provided in the embodiment of the present application includes: a drive unit 40, a mounting unit 20, and an image acquisition device 30; wherein the driving unit 40 is in transmission connection with the rotor 100, and the driving unit 40 is used for driving the rotor 100 to rotate in the casing 10.
In this embodiment, the driving unit 40 may be disposed at an end of the aircraft engine close to the compressor rotor 120 (i.e., a compressor rotor end), and the driving unit 40 is connected to the front journal 131, but the driving unit 40 may also be disposed at an end of the aircraft engine close to the turbine rotor 110 (i.e., a turbine rotor end), and the driving unit 40 is connected to the rear journal 132.
Further, the driving unit 40 may be driven manually or automatically, as long as the device can drive the rotor to rotate, and the present embodiment is not limited thereto. Illustratively, the driving unit 40 includes a hand-cranking portion and a coupler, wherein the hand-cranking portion is provided with a connecting shaft, the connecting shaft is connected with the front journal 131 through the coupler, and when in use, the hand-cranking portion is driven to rotate in a manual mode, so as to drive the rotor 100 to rotate; of course, the driving unit 40 may also include a driving motor, which is connected to the front journal 131, and the rotor 100 can be driven to rotate by starting the driving motor.
With continued reference to fig. 1, the mounting unit 20 of the present embodiment may be disposed at an end of the aircraft engine close to the turbine rotor 110, the mounting unit 20 includes a first mounting bracket 210, a first adapter shaft 220 and a synchronous driving device, the first mounting bracket 210 is used for connecting with the casing 10, the first adapter shaft 220 is rotatably connected with the first mounting bracket 210, and an axis of the first adapter shaft 220 is disposed in line with an axis of the rotor; the synchronous driving device is in transmission connection with the first rotating shaft 220, and the synchronous driving device is used for driving the first rotating shaft 220 to rotate synchronously with the rotor 100.
Further, as shown in fig. 2, the first mounting frame 210 is mainly a frame for mounting and supporting, and in some embodiments, the first mounting frame 210 includes a first fixing ring 211 and a first hub 212 located in the first fixing ring 211, and the first hub 212 is connected to the first fixing ring 211; the first fixing ring 211 is used to connect the casing 10. A plurality of first connecting rods 213 may be disposed between the first hub 212 and the first fixing ring 211, and the plurality of first connecting rods 213 are disposed around the axis of the first coupling shaft 220 at equal intervals; one end of the first connecting rod 213 is connected to the first hub 212, and the other end is connected to the first fixing ring 211, so that the first fixing ring 211 is connected to the first hub 212 via the first connecting rod 213.
Illustratively, the first fixing ring 211 is provided with a plurality of bolt holes along the circumferential direction, and is connected to the casing 10 after fastening bolts pass through the bolt holes, so as to connect the first mounting bracket 210 to the casing 10. Through the arrangement, the mounting unit can be fixed on the casing 10, and the mounting structure is simple and convenient to mount.
As shown in fig. 1 and 2, the first hub 212 is provided with a first rotation hole, and the first rotation shaft 220 is rotatably inserted into the rotation hole. Further, a first bearing 244 may be disposed between the first rotating shaft 220 and the first rotating hole for improving the stability and smoothness of the rotation of the first rotating shaft 220 in the first rotating hole.
In addition, with continued reference to fig. 1 and 2, a plurality of hanging rings 214 may be circumferentially and annularly disposed on the first fixing ring 211, and the hanging rings 214 are uniformly distributed. So set up, be convenient for hoist and mount convenient operation from different position to detection device.
Illustratively, the suspension ring 214 includes a lifting lug and a connecting portion, the lifting lug and the connecting portion are connected by a hinge shaft, the lifting lug can rotate around the hinge shaft, and the connecting portion can be connected with the first fixing ring by a bolt or a welding manner. Of course, the hanging ring 214 may also include a ring body, the ring body may be connected with the first fixing ring by welding, and of course, the ring body may also be formed as an integral structure with the first fixing ring by casting.
In other embodiments, the first mounting frame 210 may further include a steel plate and a collar, and an end of the steel plate may be connected to the casing 10 by fastening bolts, so that the first mounting frame 210 is connected to the turbine casing 10; the middle part of steel sheet is equipped with the through-hole, and the lantern ring welding is in through-hole department, and the axis of the lantern ring and the central line collineation of through-hole, first switching shaft 220 wear to establish in the lantern ring to can rotate around the lantern ring.
In this embodiment, the first rotating shaft 220 can rotate relative to the first mounting frame 210, so that it can rotate synchronously with the rotor 100 under the driving of the synchronous driving device. In some embodiments, the first coupling shaft 220 may be in transmission connection with the rear shaft diameter 132, that is, the driving unit 40 and the rotor 100 constitute a synchronous driving device, so that the first coupling shaft 220 can rotate synchronously with the rotor 100. Of course, in this embodiment, the synchronous driving device may also be another device capable of driving the first rotating shaft and the rotor 100 to rotate synchronously, which is not limited in this embodiment.
As shown in fig. 1, in the present embodiment, the image capturing device 30 is disposed on the first adapter shaft 220 and rotates with the first adapter shaft 220, and the image capturing device 30 is used for capturing an image of the blade tip of the turbine blade 140 and the inner wall of the casing 10, so as to capture the blade tip clearance according to the image.
In some embodiments, the image acquisition device 30 may include a binocular camera mounted on the first coupling shaft 220 and rotating with the first coupling shaft 220, the binocular camera being a device manufactured using the principle of binocular vision. Observing an object from two points or multiple points, acquiring images under different viewing angles, calculating the offset between pixels by utilizing the triangulation principle according to the matching relation of the pixels between the images to acquire the three-dimensional information of the object, and calculating the blade tip clearance by the method.
In other embodiments, as shown in fig. 1 and 4, the image capturing device 30 may also include a camera 310, and during the process that the synchronous driving device drives the first rotating shaft 220 to rotate synchronously with the rotor 100, the camera 310 may capture images of the corresponding blade 140 and all positions of the inner wall of the casing 10, and then through image analysis, the blade gap between the blade 140 and all positions of the inner wall of the casing 10 may be obtained.
In the above implementation manner, the tip clearance detecting device of the aircraft engine in the embodiment may further include a light source disposed on the first adapter shaft 220, and the light source is configured to generate light rays irradiating the inner walls of the casing 10 and the blade 140 corresponding to the image capturing device. So set up, can provide illumination light for image acquisition device to acquire clearer figure, and then improve aeroengine apex clearance detection device's precision.
Further, as shown in fig. 4, the light source includes a line structured light projector 320, the line structured light projector 320 includes a point light source emitter and a wave lens, and a light beam emitted from the point light source emitter is refracted by the wave lens to form a line structured light 321; the linear light forms linear light spots on the corresponding blades 140 and the inner wall of the casing 10; the line structured light projector 320 generates light rays in the same plane, and the axis of the rotor is located in the plane, that is, the line structured light projected in the tip clearance coincides with the diameter of the inner wall of the casing 10, thereby facilitating the image processing in the later period.
In other embodiments, the light source may also be an LED light source, the LED light source is mounted on the first adapter shaft, and light emitted by the LED light source irradiates between the blade to be measured and the inner wall of the casing, so as to improve the definition of the image.
The detection process of the aeroengine blade tip clearance detection device provided by the embodiment of the application is as follows: after the rotor 100 is installed in the casing 10, the image capturing device 30 is installed on the first adapter shaft 220, the installation unit 20 is installed on the casing 10 at the end of the turbine rotor 110, the image capturing device 30 is aligned with the tip clearance of the blade 140 to be tested, and the driving unit 40 is connected to the rotor 100. The driving unit 40 drives the rotor 100 to rotate, and the synchronous driving device drives the first rotating shaft 220 to rotate synchronously with the rotor 100; in this process, the image of the tip clearance of the corresponding blade 140 is acquired by the image acquiring device 30, and the acquired image is transmitted to the computer, which analyzes and calculates the tip clearance. The image obtaining device 30 can obtain the blade tip clearance between the blade 140 and the inner wall of the casing 10 by rotating one circle along with the first rotating shaft 220, so as to prevent the inter-blade clearance from exceeding the allowable range; wherein the allowable range is the largest range in which the tip clearance does not affect the performance of the aircraft engine.
Further, after the image capturing device 30 rotates with the first rotating shaft 220 for one circle, the rotation of the rotor 100 and the first rotating shaft 220 may be stopped, and then the first rotating shaft 220 rotates with respect to the rotor 100 for a certain angle, at which time the image capturing device 30 may be aligned with the next blade 140, and then the above operations may be repeated, so as to obtain the tip clearance between the next blade 140 and each side wall of the casing 10. This is repeated to obtain the tip clearance between each blade 140 and each sidewall of the casing 10.
According to the device for detecting the blade tip clearance of the aero-engine, provided by the embodiment of the application, the driving unit 40 is in transmission connection with the rotor 100, and the driving unit 40 drives the rotor 100 to rotate in the casing 10; the mounting unit 20 is arranged at one end of the turbine rotor 110, the mounting unit 20 comprises a first mounting frame 210, a first adapter shaft 220 mounted on the first mounting frame 210, and a synchronous driving device, the first adapter shaft 220 is rotatably connected with the first mounting frame 210, and the axis of the first adapter shaft 220 is arranged in line with the axis of the rotor 100; the first mounting frame 210 is connected with the casing 10, the synchronous driving device is in transmission connection with the first adapting shaft 220, and the synchronous driving device drives the first adapting shaft 220 to synchronously rotate with the rotor 100; the image acquisition device 30 is arranged on the first adapter shaft 220, the image acquisition device 30 is used for acquiring images of the blade tips of the turbine blades 140 and the inner wall of the casing 10, and the blade tip clearances between the blades 140 and the side walls of the casing can be acquired by rotating the image acquisition device 30 along with the first adapter shaft for one circle, so that the blade clearances between the blades 140 and part of the side walls of the casing 10 are prevented from exceeding an allowable range, and further the performance requirements of the engine are ensured.
Further, as shown in fig. 1 and 4, the mounting unit 20 further includes a fixing base 330, the fixing base 330 is detachably connected to the first adapter shaft 220, and the line structured light projector 320 and the image capturing device 30 are both disposed on the fixing base 330. When the linear structured light projector 320 and the image capturing device 30 are mounted on the fixing base 330 in advance, the fixing base 330 is mounted on the first adapter shaft 220, and when the linear structured light projector and the image capturing device are dismounted, the fixing base 330 can be directly dismounted. Through the above arrangement, compared with the installation mode that the linear structured light projector 320 and the image acquisition device 30 are directly installed on the first adapter shaft 220, the factor that the installation space in the casing 10 is limited is avoided, and the dismounting of the blade tip gap detection device of the aero-engine is facilitated.
As shown in fig. 4, for example, the fixing base 330 may include a mounting base 331 and a supporting base 332, where the mounting base 331 includes a first steel plate and a second steel plate, the first steel plate and the second steel plate are connected at 90 ° to form a right-angled bracket, and two end faces of the mounting bracket forming a right angle are respectively provided with a reinforcing rib to improve the strength of the mounting bracket. Be equipped with the mounting hole on the first steel sheet, the tip that first switching axle 220 deviates from rotor 100 is equipped with the location boss, is equipped with the cutting plane on the boss of location, is equipped with on the cutting plane with mounting hole matched with screw hole to twist the bolt in the mounting hole, realize fixing base 330 and first switching axle 220's being connected through the bolt. The supporting seat 332 is a plate-shaped structure, the supporting seat 332 is installed at an end portion of the second steel plate away from the first steel plate, illustratively, the supporting seat 332 is welded on the second steel plate, it is worth to say that the supporting seat and the first steel plate have a certain inclination angle, so that the supporting seat inclines towards the tip direction of the turbine blade along the first steel plate, the line-structured light projector 320 and the image acquisition device 30 are installed on the supporting seat 332, and the line-structured light projector 320 and the image acquisition device incline along the supporting plate, so that light can be arranged on the tip of the turbine blade. The above arrangement enables the fixing base 330 to be stably mounted on the first adapting shaft 220, and provides a guarantee for the stability of the image capturing device 30 and the line structured light projector 320 during the rotation process.
As shown in fig. 1, in an embodiment that the first mounting bracket 210 includes a first fixing ring 211, an end of the first adapter shaft 220 facing away from the first hub 212 is configured to be inserted into a shaft hole of the rotor 100, and a support bearing 250 configured to cooperate with the shaft hole is disposed on the first adapter shaft 220. The rear axle journal 132 is sleeved on the end of the first transfer shaft 220 through a support bearing 250, and the first transfer shaft 220 provides support and positioning for the rear axle journal 132. The rear journal 132 rotates relative to the first transfer shaft 220 through the support bearing 250. The arrangement realizes the positioning and supporting of the rear shaft neck 132, plays a centering role in the rotor 100, avoids the phenomenon that the detection result is influenced by the deformation of the rotor 100 caused by the cantilever structure of the rotor 100, and further improves the detection precision of the blade tip clearance detection device of the aeroengine.
In some possible embodiments, the synchronous driving device may include a first servo motor 230, the first servo motor 230 is disposed on the first mounting frame 210, and a main shaft of the first servo motor 230 is in transmission connection with the first adapter shaft 220. The first servo motor 230 can be controlled by the control system to rotate at a speed equal to the rotation speed of the first servo motor to achieve synchronous rotation of the first coupling shaft 220 and the rotor 100. By the arrangement, the operability and controllability of the detection device are improved, the detection process is facilitated, and meanwhile, the accuracy of the detection result is further guaranteed.
Further, as shown in fig. 2, in the embodiment where the first mounting seat 331 includes the first fixing ring 211, an end of the first transfer shaft 220 facing away from the rotor 100 is connected to one end of a driving shaft, the other end of the driving shaft is connected to a main shaft of the first servo motor 230, and a housing of the first servo motor 230 is connected to a first hub.
In other embodiments, the first hub 212 may further be provided with a positioning cover 240, the positioning cover 240 includes a positioning shaft sleeve 241 and an end cover 242 installed at one end of the positioning shaft sleeve 241, when installed, the end cover 242 is disposed away from the end of the turbine rotor 110, wherein an installation ring 243 is circumferentially disposed on an outer wall of a middle section of the positioning shaft sleeve 241, an installation hole is circumferentially disposed on the installation ring 243, a bolt hole matched with the first hub 212 is disposed on the first hub 212, and the positioning cover 240 is connected to the first hub 212 through a bolt; the end of the first hub 212 facing the rotor 100 is provided with a positioning stop hole, the diameter of the positioning stop hole is smaller than that of the first rotation hole, a first bearing 244 is arranged between the first rotation shaft 220 and the first rotation hole, one end surface of the outer ring of the first bearing 244 abuts against the hole end surface of the positioning stop hole, the outer diameter of the positioning shaft sleeve 241 is smaller than the inner diameter of the first rotation hole, and the end of the positioning shaft sleeve 241 abuts against the other end surface of the outer ring of the first bearing 244, so that the axial positioning of the first rotation shaft 220 is realized. The end cap 242 is provided with a first support ring 245, the end cap 242 is provided with a central hole, the first adapter shaft 220 penetrates through the central hole to be connected with a main shaft of the first servo motor 230, and the first servo motor 230 is connected to the end cap in a casing manner.
In the embodiment that the driving unit 40 includes the driving motor, the driving motor may be a motor with an uncontrollable rotation speed, and the rotor 100 may be driven to rotate by the motor after being powered on, correspondingly, the driving unit 40 may further include an angle encoder, and the angle encoder may implement feedback of the rotation angle of the rotor 100, and the detection parameter of the angle encoder may further be coupled to the blade tip clearance to position the blade tip clearance value of the rotor 100 in each phase, so as to analyze the reason of the change more comprehensively, and provide a basis for adjusting the rotor 100 in a later period.
During the use, in the implementation mode that driving motor is the uncontrollable motor of rotational speed and has set up angle encoder, motor drive rotor 100 rotates, and angle encoder feeds back the rotation parameter of rotor 100 to control system, and control system realizes the synchronous rotation of first switching shaft 220 and rotor 100 through the rotational speed of steerable first servo motor 230.
In other embodiments, as shown in fig. 1, the driving motor may also be a second servo motor 410, and the rotation speed of the rotor 100 can be precisely controlled and the angular displacement parameters can be obtained through the second servo motor 410, so that the controllability of the detection device is improved, and the positioning of the phase angles of different blade tip gaps is also realized.
In the embodiment where the synchronous driving device is the first servo motor 230, the first servo motor 230 drives the first spindle 220 to rotate, the second servo motor 410 drives the rotor 100 to rotate, and controlling the first servo motor 230 and the second servo motor 410 to be synchronous controls the rotor 100 and the image capturing device 30 to rotate synchronously. When the device is used, the first servo motor 230 and the second servo motor 410 are controlled to synchronously rotate, after one circle of rotation, the detection of the circumferential tip clearance of one blade 140 is completed, and the result is stored. The first servo motor 230 is driven to rotate by a certain angle independently, the image acquisition device 30 is aligned to other blades 140, then the first servo motor 230 and the second servo motor 410 are driven to rotate synchronously, after one circle is completed, the result is stored, the first servo motor 230 is driven independently again, and so on, and the detection of the circumferential blade tip clearance of all the blades 140 at the last stage of the turbine is completed. In the above arrangement, the first transfer shaft 220 and the rotor 100 are independently driven by the first servo motor 230 and the second servo motor 410 respectively, and the two servo motors are controlled to control the synchronous rotation of the rotor 100 and the first transfer shaft 220.
In some embodiments, as shown in fig. 3, the driving unit 40 is disposed at a rotor end of the compressor, and the driving unit 40 may further include a second mounting bracket 420 and a second transfer shaft 430, wherein the second mounting bracket 420 is connected to the casing 10, the second transfer shaft 430 is rotatably connected to the second mounting bracket 420, and the second transfer shaft 430 is configured to be in transmission connection with the rotor 100; the driving motor is installed on the second mounting bracket 420, and a main shaft of the driving motor is in transmission connection with the second transfer shaft 430. In the above arrangement, the second mounting bracket 420 is fixed on the casing 10, so as to provide reliable support for the driving unit 40, and prevent the rotor 100 from being deformed due to the overweight of the driving unit 40, thereby affecting the accuracy of the detection result
In this embodiment, with reference to fig. 3, the second mounting bracket 420 includes a second fixing ring 421 and a second hub 422 located in the second fixing ring 421, the second fixing ring 421 is configured to be connected to the casing 10 and is disposed opposite to the mounting unit 20, wherein a plurality of second connecting rods 423 are disposed on the second hub 422, the plurality of second connecting rods 423 are disposed around the axis of the second transfer shaft 430 at equal intervals, one end of each second connecting rod 423 is connected to the second hub 422, the other end of each second connecting rod 423 is connected to the second fixing ring 421, and the second fixing ring 421 is connected to the second hub 422 through the second connecting rods 423.
As shown in fig. 1, the second hub 422 is provided with a second rotation hole, the second transfer shaft 430 is rotatably disposed in the second rotation hole, and a second bearing may be disposed between the second rotation hole and the second transfer shaft 430, so that the second transfer shaft 430 can rotate more smoothly.
Continuing to refer to fig. 1, one end of the second transfer shaft 430 is used for being in transmission connection with the rotor 100, wherein a transfer portion is arranged between the second transfer shaft 430 and the front journal 131, a groove is formed at one end of the transfer portion, the front journal 131 is installed in the groove, a set screw is installed on the side wall of the transfer portion along the radial direction, and the end portion of the set screw is screwed into a corresponding threaded hole on the side wall of the rotor 100 to realize the connection between the front journal 131 and the transfer portion; the bottom of the groove is provided with a bottom plate, the bottom plate is connected with one end of the second transfer shaft 430 in a screwing or riveting mode, and the arrangement provides reliable guarantee for transmission connection between the driving shaft and the rotor 100.
Further, a second supporting ring 424 is arranged on the second hub 422, one end of the second supporting ring 424 is fixed on the second hub 422, and the other end of the second supporting ring 424 is connected with the casing of the driving motor, so that the driving motor is fixed and supported.
In the description herein, reference to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present application, and that variations, modifications, substitutions and alterations may be made to the above embodiments by those of ordinary skill in the art within the scope of the present application.
Claims (10)
1. The utility model provides an aeroengine apex clearance detection device which characterized in that includes: a drive unit, a mounting unit, and an image acquisition device;
the driving unit is used for being in transmission connection with the rotor and is used for driving the rotor to rotate in the casing;
the mounting unit is used for being arranged at one end of a turbine rotor and comprises a first mounting frame, a first adapter shaft and a synchronous driving device, the first mounting frame is used for being fixedly connected with a casing, the first adapter shaft is rotatably connected with the first mounting frame, and the axis of the first adapter shaft and the axis of the rotor are arranged in a collinear manner; the synchronous driving device is connected with the first adapter shaft and is used for driving the first adapter shaft and the rotor to synchronously rotate;
the image acquisition device is arranged on the first adapter shaft and used for acquiring images of the blade tips of the turbine blades and the inner wall of the casing so as to acquire the distance between the blade tips and the inner wall of the casing according to the images.
2. The aero engine tip clearance detection device of claim 1 further comprising a light source disposed on the first spindle, the light source configured to emit light between the inner casing wall and the blade.
3. The aircraft engine tip clearance detection apparatus of claim 2, wherein the light source comprises a line structured light projector, the light rays generated by the line structured light projector lying in a common plane and the axis of the rotor lying in that plane.
4. The aero-engine blade tip clearance detection device according to claim 3, wherein the mounting unit further comprises a fixing base, the fixing base is detachably connected to the first adapter shaft, and the line structured light projector and the image capturing device are both disposed on the fixing base.
5. The aircraft engine blade tip clearance detection device of claim 1, wherein the synchronous drive device comprises a first servo motor, the first servo motor is arranged on the first mounting frame, and a main shaft of the first servo motor is in transmission connection with the first adapter shaft.
6. The aircraft engine blade tip clearance detection device of claim 1, wherein the first mounting bracket comprises a first fixed ring and a first hub located in the first fixed ring, the first hub being fixedly connected to the first fixed ring; the first fixing ring is used for connecting the casing;
the first hub is provided with a first rotating hole, and the first rotating shaft is rotatably arranged in the rotating hole in a penetrating mode.
7. The aeroengine blade tip clearance detection device of claim 6, wherein the circumferential ring of the first fixed ring is provided with a plurality of lifting rings which are evenly distributed.
8. The aircraft engine blade tip clearance detection device of claim 6, wherein the first adapter shaft is further rotatably mounted in a shaft hole of the rotor, and a support bearing matched with the shaft hole is arranged on the first adapter shaft.
9. The aero-engine blade tip clearance detection device according to any one of claims 1 to 8, wherein the driving unit is configured to be disposed at a rotor end of a compressor, the driving unit includes a second servo motor, a second mounting bracket and a second adapter shaft, the second mounting bracket is connected to the casing, the second adapter shaft is rotatably connected to the second mounting bracket, and the second adapter shaft is configured to be in transmission connection with the rotor; the second servo motor is installed on the second mounting rack, and a main shaft of the second servo motor is in transmission connection with the second adapter shaft.
10. The aircraft engine blade tip clearance detecting device according to claim 9, wherein the second mounting bracket includes a second fixing ring and a second hub located in the second fixing ring, the second fixing ring is configured to be connected to the casing, a second rotating hole is provided in the second hub, the second adapter shaft is rotatably disposed in the second rotating hole, and the second servo motor is connected to the second hub.
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| CN202111350602.6A CN114152204B (en) | 2021-11-15 | 2021-11-15 | Aero-engine blade tip clearance detection device |
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| CN202111350602.6A CN114152204B (en) | 2021-11-15 | 2021-11-15 | Aero-engine blade tip clearance detection device |
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