CN113624472B - Measuring device for guide vane adjusting mechanism of air compressor - Google Patents
Measuring device for guide vane adjusting mechanism of air compressor Download PDFInfo
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- CN113624472B CN113624472B CN202110888328.1A CN202110888328A CN113624472B CN 113624472 B CN113624472 B CN 113624472B CN 202110888328 A CN202110888328 A CN 202110888328A CN 113624472 B CN113624472 B CN 113624472B
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- 230000007246 mechanism Effects 0.000 title claims abstract description 27
- 238000007689 inspection Methods 0.000 claims abstract description 45
- 238000005259 measurement Methods 0.000 claims abstract description 16
- 238000003825 pressing Methods 0.000 claims description 52
- 239000006185 dispersion Substances 0.000 claims description 21
- 238000009434 installation Methods 0.000 claims description 14
- 238000013461 design Methods 0.000 abstract description 8
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 9
- 238000010586 diagram Methods 0.000 description 6
- 238000012545 processing Methods 0.000 description 3
- 230000033001 locomotion Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 238000009827 uniform distribution Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
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- 230000002035 prolonged effect Effects 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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Abstract
The invention discloses a measuring device of a guide vane adjusting mechanism of a compressor, which relates to the technical field of aeroengine assembly and comprises a blade angle dispersity inspection tool assembled in a compressor casing, and the tool is used for inspecting the actual mounting angle of each blade in the compressor casing; the angle-travel relation checking tool assembled outside the compressor casing is used for measuring the relation between the travel of the actuator cylinder and the angle of the guide vane before the assembly of the engine by simulating the working state of the actuator cylinder of the engine. According to the invention, the radial height plate of the tool for checking the blade angle dispersity can slide along the circumferential direction between the first flange and the compressor casing, the overall required measurement time is short, the mass production efficiency of the subsequent engine is effectively improved, the principle is simple, and the professional requirement on operators is low; the angle-travel relation checking tool can identify whether guide vane adjustment meets design requirements before the engine assembly, so that factory return is prevented from being repeated, and a large number of secondary works are avoided.
Description
Technical Field
The invention belongs to the technical field of aero-engine assembly, and particularly relates to a measuring device for a guide vane adjusting mechanism of a gas compressor.
Background
In the design of the compressor, the adjustable guide vane is used as an active means, so that the stall and surge of the compressor under the non-design working condition can be effectively avoided, the performance of the non-design working condition of the compressor can be effectively improved through reasonable adjustment of the angle of the guide vane, and the stable working range of the compressor is enlarged.
The guide vane adjusting mechanism in the prior art mainly comprises a linkage ring, a rocker arm, an operating lever, a connecting rod and the like, wherein the operating lever is driven by the actuating cylinder through the connecting rod, and the operating lever is connected with the linkage ring and the actuating cylinder through the connecting rod to convert the linear motion of the actuating cylinder into the rotation of the linkage ring, so that the change of the guide vane angle is controlled.
The measurement of the guide vane adjusting mechanism mainly comprises guide vane angle dispersion degree inspection and angle-travel relation inspection. At present, the inspection mode of the angle dispersion degree of the guide vane mainly measures the blade profile of a specific height of the blade through three coordinates and compares the blade profile with a theoretical blade profile, so that the angle dispersion degree of the blade is obtained; however, this method is heavy, takes a long time to calculate, and requires a high level of skill on the inspection staff. The angle-stroke relation check is to record the corresponding stroke of the actuator cylinder by manually rotating the operating rod by taking the dial or the theoretical reference hole as a reference after the engine assembly is mounted on the test vehicle table; the mode has certain errors due to manual operation, and whether the design requirements are met or not can not be identified before the assembly of the engine, so that problems occur, and the engine can only be checked by returning to a factory at a lower stage, so that a large number of secondary works are caused.
Therefore, the invention provides a measuring device for a guide vane adjusting mechanism of a compressor, so as to solve the problems in the background art.
Disclosure of Invention
The invention aims to provide a measuring device for a guide vane adjusting mechanism of a compressor, which aims to solve the following technical problems:
1) The three-coordinate metering guide vane angle dispersity method can bring huge workload along with the increase of the number of adjustable guide vane stages and the number of blades, and the corresponding metering time can be greatly prolonged, so that the mass production progress of the subsequent engine is finally influenced; and the method has certain requirements on the configuration of the inspector, and needs the comparison work of professional technicians, and part of conventional inspectors cannot complete the work.
2) According to the method for checking the angle-travel relation of the bench calibration, the actuating cylinder cannot perform active travel propulsion after being electrified on the test bench, so that the calibration work can be performed only by manually rotating the operating rod, and the transmission path in the calibration process is 'operating rod-connecting rod-actuating cylinder', which is opposite to the active-driven relation of an actual guide vane mechanism, so that a certain error exists in bench calibration, and the actual guide vane angle-actuating cylinder travel relation cannot be accurately reflected; in addition, the method can not identify whether the angle-stroke relation meets the design requirement before the assembly of the engine, and once the problem occurs, the engine can only be checked by returning to the factory, so that a large amount of secondary work is caused.
According to one aspect of the invention, a measuring device of a guide vane adjusting mechanism of a compressor is provided, and the measuring device is assembled with a compressor casing and comprises a blade angle dispersity inspection tool assembled in the compressor casing and used for inspecting the actual installation angle of each blade in the compressor casing; and the angle-stroke relation checking tool is assembled outside the compressor casing and is used for measuring the relation between the stroke of the actuator cylinder and the angle of the guide vane before the assembly of the engine by simulating the working state of the actuator cylinder of the engine.
According to an exemplary embodiment of the present invention, the blade angle dispersion checking fixture includes a first flange assembled on the compressor casing by screws, a radial height plate assembled between the first flange and the compressor casing and forming a sliding connection, a support block slidably connected on an extension of the radial height plate, a first pressing plate forming a rotational connection with the support block by the first pin, and a dial.
According to another exemplary embodiment of the present invention, the supporting block is composed of an assembling portion at the top and a supporting portion at the bottom, the assembling portion is sleeved on the extension section with the scale marks and forms sliding connection, a through hole adapted to the extension section is formed in the assembling portion, a scale viewing window is formed in the top of the through hole, and a threaded hole is formed in the side face of the through hole; the supporting part is in a rod-shaped structure, the bottom of the supporting part is fixedly connected with a first bolt, and the top of the supporting part is fixedly connected with a dial.
According to another exemplary embodiment of the present invention, the first pressing plate is in clearance fit with the first bolt, and a side surface of the first pressing plate is profiled according to a theoretical blade profile and abuts against the blade.
According to another exemplary embodiment of the present invention, the inspection steps of the blade angle dispersion degree inspection tool are as follows:
s1: mounting a blade angle dispersity inspection tool on a compressor casing;
s2: before use, checking and calibrating the initial position of the tool for checking the angular dispersion degree of the blade;
s3: observing the scales of the radial height plate, pushing the supporting block to the radial height position of the blade to be measured, and screwing down the screw to fix the supporting block;
s4: adjusting the blade measurement angle, sliding the supporting block along the circumferential direction of the first flange, rotating the first pressing plate to enable the blade profile on the right side of the first pressing plate to cling to the first measurement blade, and screwing down a screw to fix the position of the supporting block;
s5: reading and recording angle values corresponding to the radial height plate and the dial;
s6: and (5) sequentially sliding the radial height plates to the positions of the rest blades, and repeating the steps S2-S5 to obtain the angular dispersion degree of each blade.
According to another exemplary embodiment of the present invention, the angle-stroke relationship checking fixture includes a second flange, a supporting seat, a second pressing plate, an actuating cylinder, a joint bearing and a second bolt, wherein the second flange is fixed on the compressor casing through a screw, one side of the second flange, which is close to the compressor casing, is an arc section, one of two angles of the second flange, which is far away from the arc section, is provided with a right-angle unfilled corner inwards, and two surfaces perpendicular to the right-angle unfilled corner are an a reference surface and a B reference surface respectively.
According to another exemplary embodiment of the present invention, the support seat is fixedly connected to the second flange, the relative position of the support seat and the second flange is adapted to the reference plane a and the reference plane B, a positioning groove is provided on one side of the support seat away from the second flange, and symmetrically provided pin holes are provided at the bottom of the positioning groove.
According to another exemplary embodiment of the present invention, a second pressing plate is fixedly connected to one side of the support seat provided with the positioning groove, a waist-shaped groove adapted to the pin hole of the positioning groove is formed in the second pressing plate, and scale marks with initial positions of zero are arranged on the second pressing plate along the waist-shaped groove; the positioning groove is internally penetrated with an actuating cylinder, the actuating cylinder is provided with a pin hole matched with the waist-shaped groove, the positioning groove, the actuating cylinder and the waist-shaped groove are simultaneously penetrated by a second bolt, one end of the actuating cylinder is provided with a joint bearing, and the joint bearing is connected with an engine guide vane adjusting mechanism.
According to another exemplary embodiment of the present invention, the checking steps of the angle-stroke relation checking fixture are as follows:
s1: installing an angle-stroke relation checking tool on the compressor casing;
s2: checking and calibrating the initial position of the tool for checking the angle-stroke relation before using the tool;
s3: the knuckle bearing on the actuator cylinder is connected with the actuator cylinder connecting rod through a bolt;
s4: and pulling out the second bolt from the pin hole of the supporting seat, pushing the actuating cylinder to linearly move in the positioning groove of the supporting seat, driving the operating rod to rotate, enabling the second bolt to move along with the actuating cylinder, and recording the stroke of the second pressing plate and the corresponding guide vane dial reading.
According to another exemplary embodiment of the present invention, the measuring steps of the compressor vane adjusting mechanism measuring device are as follows:
s1: before use, the tool initial position checking and calibration are respectively carried out on the angle-travel relation checking tool and the blade angle dispersity checking tool;
s2: the angle-travel relation checking tool and the blade angle dispersity checking tool are assembled on the compressor casing;
s3: pulling out a second bolt of the angle-stroke relation checking tool from a pin hole of a supporting seat, pushing an actuating cylinder to linearly move in a positioning groove of the supporting seat, driving an operating rod to rotate, enabling the second bolt to move along with the actuating cylinder, and recording stroke scales of a second pressing plate corresponding to the second bolt;
s4: measuring the blade angle corresponding to the stroke of the actuating cylinder at the moment through a blade angle dispersity inspection tool;
s5: pushing the actuator cylinder to the rest of the actuator cylinder strokes to be measured again, and repeating the steps S2 and S3 to obtain the installation angles of the blades corresponding to the rest of the actuator cylinder strokes.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the invention, by arranging the blade angle dispersity inspection tool and the angle-travel relation inspection tool, the angle dispersity and the angle-travel relation of the guide vane can be inspected by two tools before the assembly of the engine, whether the processing and the installation of the guide vane meet the design requirements can be detected, and the pneumatic performance and the consistency of the air compressor are ensured.
2. According to the blade angle dispersity inspection tool, the radial height plate can slide between the first flange and the compressor casing, a plurality of guide vanes can be quickly transposed, the overall required measurement time is short, and the mass production efficiency of the subsequent engine is effectively improved; moreover, the principle of the blade angle dispersity inspection tool is simple and easy to understand, the professional requirement on operators is low, and conventional inspectors can finish the angle dispersity measurement of the guide vane by means of the blade angle dispersity inspection tool.
3. The angle-travel relation checking tool provided by the invention can identify whether the guide vane adjustment meets the design requirement before the assembly of the engine, prevent the return to the factory from being repeated, avoid a large amount of secondary work and save time and cost.
Drawings
The present invention is further described below with reference to the accompanying drawings for the convenience of understanding by those skilled in the art.
FIG. 1 is a schematic diagram of an overall structure of a compressor vane adjustment mechanism measurement device;
FIG. 2 is a schematic view of a blade mounting angle;
FIG. 3 is a schematic diagram of the overall structure of a blade angle dispersion inspection tool;
FIG. 4 is an exploded view of a blade angle dispersion inspection tool;
FIG. 5 is an assembly schematic diagram of a blade angle dispersion inspection tool;
FIG. 6 is a schematic diagram of the overall structure of the angle-travel relationship inspection tool;
FIG. 7 is a view in the direction A of FIG. 6;
FIG. 8 is an exploded view of an angle-travel relationship inspection tool;
FIG. 9 is an assembly schematic diagram of an angle-travel relationship inspection tool;
fig. 10 is a schematic diagram of calibration of the initial position of the angle-travel relation inspection tool.
In the figure: 1. blade angle dispersity inspection tool; 2. checking a tool for the angle-travel relation; 3. a compressor casing;
101. a first flange; 102. a radial height plate; 103. a support block; 104. a first platen; 105. a first latch; 106. a dial;
201. a second flange; 202. a support base; 203. a second pressing plate; 204. an actuator cylinder; 205. a knuckle bearing; 206. and a second bolt.
Detailed Description
The technical solution of the present invention will be further specifically described below by way of examples with reference to the accompanying drawings in order to make the objects, technical solutions and advantages of the present invention more apparent. In the specification, the same or similar reference numerals denote the same or similar components. The following description of embodiments of the present invention with reference to the accompanying drawings is intended to illustrate the general inventive concept and should not be construed as limiting the invention to a compressor vane adjustment mechanism measurement device.
Furthermore, in the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the present disclosure. It may be evident, however, that one or more embodiments may be practiced without these specific details. In other instances, well-known structures and devices are shown in the drawings in order to simplify the drawings.
According to one general technical concept of the present invention, as shown in fig. 1 to 10, there is provided a measuring apparatus for a guide vane adjusting mechanism of a compressor, comprising a blade angle dispersion checking fixture 1 assembled inside a compressor casing 3, as shown in fig. 2, the blade angle dispersion checking fixture 1 is used to check the actual installation angle of each blade, i.e., the angle between the process chord length of the blade and the axis of the engine.
The blade angle dispersity inspection tool 1 is formed by assembling a first flange 101, a radial height plate 102, a supporting block 103, a first pressing plate 104, a first bolt 105 and a dial 106, threaded holes which are uniformly distributed are formed in a compressor casing 3, the first flange 101 plate corresponds to the threaded holes in the compressor casing 3, the threaded holes are uniformly formed in the first flange 101 plate, the first flange 101 plate covers the compressor casing 3 during installation, screws are arranged in the threaded holes, the screws can be simultaneously connected with the threaded holes in the compressor casing 3 and the first flange 101 plate, and the first flange 101 plate is fixed on the compressor casing 3; an annular groove is formed in one surface, which is attached to the compressor casing 3, of the first flange 101 to be clamped with the radial height plate 102, and a circle of uniformly distributed threaded holes are formed in the inner ring of the threaded hole for assembling the compressor casing 3 to be used for fixing the radial height plate 102; the bottom of the inner circular surface of the first flange 101 is provided with scale marks for measuring the angular position of the radial height plate 102, and then the circumferential uniform distribution condition of each blade is obtained.
The radial height plate 102 is formed by processing a section of arc-shaped plate machine, two sections of annular steps are respectively formed at two ends, which are mutually far away from each other, of the upper surface and the lower surface of the radial height plate 102, one of the annular steps is assembled in an annular groove of the first flange 101 disc so that the radial height plate 102 can slide along the circumferential direction, the other annular step is abutted on the compressor casing 3, so that the inner circular surface of the radial height plate 102 is overlapped with the inner circular surface of the first flange 101, and meanwhile, the top of the inner circular surface of the radial height plate 102 extends to one side by taking the central axis as a starting point; the central axis is also provided with an extension section pointing to the circle center, and the extension section is a regular polygon rod with scales.
The support block 103 is arranged on the extension section, the support block 103 consists of an assembly part at the top and a support part at the bottom, the assembly part is a cube as a whole, a polygonal through hole matched with the extension section is formed, and a threaded hole communicated with the polygonal through hole is formed in one side of the support part perpendicular to the support part; when in installation, the supporting block 103 is sleeved on the extension section, and the supporting block 103 and the extension section are in clearance fit so that the supporting block 103 can slide smoothly on the extension section; a scale viewing window is arranged at the bottom of the assembly part; when the blade radial height measuring device is used, after the supporting block 103 reaches a calibration position, a screw is screwed into a threaded hole on the side surface, so that the screw is abutted on the extension section, and the axial movement of the supporting block 103 on the extension section is limited to fix the supporting block 103 at the position of the blade radial height to be measured; the support part is in a rod-shaped structure, and the tail part of the support part is provided with a pin hole consistent with the direction of the extension section; the supporting block 103 is welded with a dial 106 on top of the supporting bar to cooperate with the first pressure plate 104 for measuring the blade mounting angle.
The support block 103 is provided with a first pressing plate 104, the first pressing plate 104 is also provided with a pin hole, the pin holes of the support block 103 and the first pressing plate 104 are simultaneously penetrated by a first bolt 105, and the first bolt 105 can be fixedly connected with the support block 103 or can be in interference fit with the support block 103 to prevent the relative rotation of the first bolt 105 and the support block 103; meanwhile, the first pressing plate 104 is in clearance fit with the first bolt 105, so that the first pressing plate 104 can rotate around the first bolt 105; the pointer is arranged at the top of the first pressing plate 104, and meanwhile, one side surface of the first pressing plate 104 is subjected to profile processing according to a theoretical blade profile, so that the first pressing plate 104 can be attached to a measuring blade, and after the attachment is stable, the rotation angle of the first pressing plate 104, namely the blade mounting angle, can be directly read.
Next, the inspection procedure of the blade angle dispersion degree inspection tool 1 will be described in detail, including the following steps:
s1: the blade angle dispersity inspection tool 1 is installed on a compressor casing 3;
s2: before use, checking and calibrating the initial position of the tool for checking the angular dispersion degree of the blade 1, and checking whether the special tool dial 106 is zero or not when the first pressing plate 104 is parallel to the axis of the engine;
s3: by observing the scales of the radial height plate 102, pushing the supporting block 103 to the radial height position of the blade to be measured, and tightening the screw to fix the supporting block 103;
s4: rotating the control rod to the angle required to be measured by all the blade rotation, sliding the supporting block 103 along the circumferential direction of the first flange 101, rotating the first pressing plate 104, enabling the blade profile on the right side of the first pressing plate 104 to cling to the first measuring blade, and screwing down the screw to fix the position of the supporting block 103;
s5: reading and recording the corresponding angle values of the radial height plate 102 and the dial 106;
s6: and loosening the screw, pushing the supporting block 103 outwards until the supporting block does not interfere with the blades, sliding the radial height plate 102 to the second blade, and repeating the steps S2-S5 to obtain the angle value of the supporting block 103 and the dial 106 corresponding to each blade, namely obtaining the circumferential position uniform distribution condition of the blades and the angle dispersion degree of each blade.
The invention also comprises an angle-travel relation checking tool 2 assembled outside the compressor casing 3, and as shown in fig. 6-10, the working state of the engine actuator 204 is simulated by designing a special actuator 204 tool so as to know the relation between the travel of the actuator 204 and the angle of the guide vane before the assembly of the engine.
The angle-stroke relation checking tool 2 is formed by assembling a second flange 201, a supporting seat 202, a second pressing plate 203, an actuating cylinder 204, a joint bearing 205 and a second bolt 206, wherein one side of the second flange 201 is an arc section, the size of the arc section is matched with that of the compressor casing 3, and four threaded holes are uniformly formed in the arc section along the circumferential direction, so that the second flange 201 is fixed on the compressor casing 3 through screws; one of two corners of the second flange 201 far away from the arc section is provided with a right-angle unfilled corner towards the inside of the second flange 201, two sides perpendicular to the right-angle unfilled corner serve as two reference surfaces, one surface of the two reference surfaces, which is intersected with the adjacent surface of the arc section, is a B reference surface, and the other surface of the two reference surfaces is an A reference surface.
The supporting seat 202 is welded on the second flange 201, during welding, the arc section is positioned at the bottom, the right-angle unfilled corner is positioned at the upper right corner, the installation position of the supporting seat 202 is calculated through the reference surface A and the reference surface B, and the supporting seat 202 is placed at the calibration position and welded together; a locating groove is formed in the center of the surface, away from the welding surface, of the supporting seat 202, and symmetrically arranged locating holes are formed in the bottom of the locating groove; the supporting seat 202 is covered with an adaptive second pressing plate 203 on the surface provided with the positioning groove, the second pressing plate 203 and the supporting seat 202 are fixed together through screws, a waist-shaped groove matched with the positioning hole on the positioning groove is also formed in the second pressing plate 203, a scale mark is further arranged on the edge of the waist-shaped groove, and the initial position of the scale mark is zero; the positioning groove is provided with an actuator cylinder 204, the actuator cylinder 204 is in transition fit or clearance fit with the positioning groove, so that the actuator cylinder 204 can move in a straight line in the positioning groove, and the actuator cylinder 204 is provided with a pin hole at a position matched with the waist-shaped groove for assembling a second bolt 206; meanwhile, the second bolt 206 is also matched with the scale mark on the second pressing plate 203, and the corresponding stroke of the actuator cylinder 204 can be directly read out on the scale mark through the second bolt 206; one end of the actuator cylinder 204 is also provided with a knuckle bearing 205, and the knuckle bearing 205 is connected with an engine guide vane adjusting mechanism.
Further, as shown in fig. 10, the components related to the joint bearing 205 and the compressor casing 3 have mounting position dimensions L1 and L3, the components related to the joint bearing 205 and the compressor casing 3 have mounting position dimensions L2 and L4, and the central axis of the actuator cylinder 204 has a mounting position angle θ with respect to the components related to the compressor casing 3.
Next, the inspection procedure of the angle-stroke relation inspection tool 2 will be described in detail, including the following steps:
s1: the angle-travel relation checking tool 2 is installed on the compressor casing 3, the second flange 201 is connected with the compressor casing 3 through bolts, and the assembly is shown in an opinion chart 9;
s2: before using, checking the tool 2 according to the angle-travel relation, checking and calibrating the initial position of the tool, and sequentially penetrating a second bolt 206 into a waist-shaped groove of a second pressing plate 203, a pin hole of an actuating cylinder 204 and a right side pin hole of a supporting seat 202, and checking the installation position dimensions (L1-L4 and theta) shown in FIG. 10 at the moment to ensure that the installation position dimensions are consistent with the engine;
s3: a knuckle bearing 205 on the actuator cylinder 204 is connected with a connecting rod bolt of the actuator cylinder 204;
s4: the second bolt 206 is pulled out of the pin hole of the supporting seat 202 (at this time, the second bolt 206 is still in the pin hole of the actuator cylinder 204), the actuator cylinder 204 is pushed to move linearly in the positioning groove of the supporting seat 202, so as to drive the operating rod to rotate, and the second bolt 206 moves along with the actuator cylinder 204, so that the stroke of the second pressing plate 203 and the corresponding guide vane dial 106 reading are recorded.
Next, as shown in fig. 1, a step of performing a combined inspection of the blade angle dispersion degree inspection tool 1 and the angle-stroke relation inspection tool 2 is described in detail, wherein both sets of inspection tools are assembled on the compressor casing 3 during the combined inspection, the blades are rotated by pushing the actuator 204 of the angle-stroke relation inspection tool 2, and then the mounting angle of the blades at this time is measured by the blade angle dispersion degree inspection tool 1, and the measurement steps are as follows:
s1: before use, the tool initial position checking and calibration are needed to be carried out on the angle-travel relation checking tool 2 and the blade angle dispersity checking tool 1 respectively:
angle-travel relation inspection tool 2: the second plug 206 sequentially penetrates through the waist-shaped groove of the second pressing plate 203, the pin hole of the actuator cylinder 204 and the right side pin hole of the supporting plate, and the installation position dimensions (L1-L4, theta) shown in FIG. 10 are checked at this time to ensure that the installation position dimensions are consistent with the engine;
special frock of blade angle dispersion degree: checking whether the special tool dial 106 is zeroed when the first press plate 104 is parallel to the engine axis;
s2: the angle-stroke relation checking tool 2 and the blade angle dispersity checking tool 1 are assembled on the compressor casing 3, and a knuckle bearing 205 on an actuator cylinder 204 of the angle-stroke relation checking tool 2 is connected with a connecting rod bolt of the actuator cylinder 204, as shown in fig. 9;
s3: firstly, pulling a second bolt 206 of the angle-stroke relation checking tool 2 out of a pin hole of a supporting seat 202 (at the moment, the second bolt 206 is still in a pin hole of an actuator cylinder 204), pushing the actuator cylinder 204 along the arrow direction of fig. 1, and enabling the actuator cylinder 204 to move linearly in a positioning groove of the supporting seat 202 so as to drive an operating rod to rotate, wherein the second bolt 206 moves along with the actuator cylinder 204, and recording stroke scales (namely, the stroke of the actuator cylinder 204) of a second pressing plate 203 corresponding to the second bolt 206;
s4: the blade angle corresponding to the stroke of the actuator cylinder 204 at this time is measured by the blade angle dispersity inspection tool 1, and the specific operation is as follows:
a) Sliding the supporting block 103 to the radial height position of the blade to be measured (observing the scale of the radial height plate 102), and screwing the screw to fix the supporting block 103;
b) Sliding the supporting block 103 along the circumferential direction of the first flange 101 and rotating the first pressing plate 104, so that the blade profile on the right side of the first pressing plate 104 is tightly attached to the first measuring blade, screwing the screw on the first flange 101 to fix the position of the supporting block 103, and reading the angle value corresponding to the dial 106 (namely the mounting angle of the first blade);
c) Loosening a screw, pushing the supporting block 103 to the center of the compressor casing 3 until the supporting block does not interfere with the blades, sliding the radial height plate 102 to the second blade along the circumferential direction of the first flange 101, and repeating the steps to obtain the installation angle of each blade;
s5: and pushing the actuator cylinder 204 along the arrow direction in fig. 1 again until the second actuator cylinder 204 stroke to be measured is reached, and repeating the steps S2 and S3 to obtain each blade mounting angle corresponding to the second actuator cylinder 204 stroke, so that a plurality of blade mounting angles corresponding to the actuator cylinder 204 strokes can be obtained repeatedly.
While the foregoing is directed to embodiments of the present invention, other and further details of the invention may be had by the present invention, it should be understood that the foregoing description is merely illustrative of the present invention and that no limitations are intended to the scope of the invention, except insofar as modifications, equivalents, improvements or modifications are within the spirit and principles of the invention.
Claims (9)
1. A measuring device for a compressor vane adjusting mechanism, said measuring device being assembled with a compressor casing (3), characterized in that it comprises:
the blade angle dispersity inspection tool (1) is assembled in the compressor casing (3) and is used for inspecting the actual installation angle of each blade in the compressor casing (3);
the blade angle dispersity inspection tool (1) comprises a first flange (101), a radial height plate (102), a supporting block (103), a first pressing plate (104), a first bolt (105) and a dial (106), wherein the first flange (101) is assembled on a compressor casing (3) through screws, the radial height plate (102) is assembled between the first flange (101) and the compressor casing (3) and forms sliding connection, the supporting block (103) is connected onto an extension section of the radial height plate (102) in a sliding manner, the first pressing plate (104) is connected with the supporting block (103) in a rotating manner through the first bolt (105), the supporting block (103) is composed of an assembling part at the top and a supporting part at the bottom, the supporting part is in a rod-shaped structure, the top of the supporting part is fixedly connected with the dial (106), one side surface of the first pressing plate (104) is processed according to a theoretical blade profile, so that the first pressing plate (104) can be attached to a measuring blade, and after attaching is stable, the first pressing plate (104) can be directly read out to rotate the dial (104);
the angle-travel relation checking tool (2) is assembled outside the compressor casing (3), and the angle-travel relation checking tool (2) measures the relation between the travel of the actuator cylinder (204) and the angle of the guide vane by simulating the working state of the actuator cylinder (204);
the angle-travel relation inspection tool (2) comprises a second flange (201), a supporting seat (202), a second pressing plate (203), an actuating cylinder (204), a joint bearing (205) and a second bolt (206), wherein the second flange (201) is fixed on a compressor casing (3) through screws, the supporting seat (202) is fixedly connected to the second flange (201), a positioning groove is formed in one side, far away from the second flange (201), of the supporting seat (202), a second pressing plate (203) is fixedly connected to one side, provided with a positioning groove, of the second pressing plate (203), a waist-shaped groove matched with a pin hole of the positioning groove is formed in the second pressing plate, the actuating cylinder (204) penetrates through the positioning groove, the actuating cylinder (204) and the waist-shaped groove, one end of the actuating cylinder (204) is provided with the joint bearing (205), the joint bearing (205) is connected with an engine guide vane adjusting mechanism, the second pressing plate (203) is provided with a guide vane (203) on the edge of the waist-shaped groove, the guide vane (206) can be directly read out by corresponding scales (106) through corresponding scales (106).
2. The measuring device of the guide vane adjusting mechanism of the compressor according to claim 1, wherein an assembling part of the supporting block (103) is sleeved on the extension section with the scale marks and forms sliding connection, a through hole matched with the extension section is formed in the assembling part, a scale viewing window is formed in the top of the through hole, and a threaded hole is formed in the side face of the through hole; the supporting part is in a rod-shaped structure, the bottom of the supporting part is fixedly connected with a first bolt (105), and the top of the supporting part is fixedly connected with a dial (106).
3. The measuring device of the guide vane adjusting mechanism of the compressor according to claim 2, wherein a clearance fit is formed between the first pressing plate (104) and the first bolt (105), and the side surface of the first pressing plate (104) is molded according to a theoretical blade profile and is abutted against the blade.
4. A compressor vane adjustment mechanism measuring device according to any one of claims 2-3, characterized in that the step of checking the blade angle dispersion checking fixture (1) is as follows:
s1: the blade angle dispersity inspection tool (1) is installed on a compressor casing (3);
s2: before use, checking and calibrating the initial position of the tool for checking the angular dispersion degree of the blade (1);
s3: observing the scales of the radial height plate (102), pushing the supporting block (103) to the radial height position of the blade to be measured, and screwing down the screw to fix the supporting block (103);
s4: adjusting the blade measurement angle, sliding the supporting block (103) along the circumferential direction of the first flange (101) and rotating the first pressing plate (104), enabling the blade profile on the right side of the first pressing plate (104) to cling to the first measurement blade, and screwing down a screw to fix the position of the supporting block (103);
s5: reading and recording the corresponding angle values of the radial height plate (102) and the dial (106);
s6: and (5) sequentially sliding the radial height plates (102) to the positions of the rest blades, and repeating the steps S2-S5 to obtain the angular dispersion degree of each blade.
5. The measuring device of the guide vane adjusting mechanism of the compressor according to claim 1, wherein one side of the second flange (201) close to the compressor casing (3) is an arc section, one of two corners of the second flange (201) far away from the arc section is provided with a right-angle unfilled corner inwards, and two surfaces perpendicular to the right-angle unfilled corner are an A reference surface and a B reference surface respectively.
6. The measuring device of the guide vane adjusting mechanism of the compressor according to claim 5, wherein the relative position of the supporting seat (202) and the second flange (201) is matched with the reference surface A and the reference surface B, and symmetrically arranged pin holes are formed at the bottom of the positioning groove.
7. The compressor vane adjustment mechanism measurement device of claim 6, wherein the actuator cylinder (204) is provided with a pin hole adapted to the waist-shaped groove.
8. The compressor vane adjustment mechanism measurement device according to any one of claims 5 to 7, wherein the angle-stroke relationship inspection tool (2) comprises the following inspection steps:
s1: the angle-travel relation checking tool (2) is arranged on the compressor casing (3);
s2: checking and calibrating the initial position of the tool (2) for checking the angle-stroke relation before using;
s3: a knuckle bearing (205) on the actuator cylinder (204) is connected with a connecting rod bolt of the actuator cylinder (204);
s4: and pulling out the second bolt (206) from the pin hole of the supporting seat (202), pushing the actuating cylinder (204) to linearly move in the positioning groove of the supporting seat (202), driving the operating rod to rotate, enabling the second bolt (206) to move along with the actuating cylinder (204), and recording the stroke of the second pressing plate (203) and the corresponding guide vane dial (106) reading.
9. The compressor vane adjustment mechanism measurement device of claim 1, wherein the compressor vane adjustment mechanism measurement device comprises the following measurement steps:
s1: before use, checking and calibrating the initial positions of the tool for checking the angle-stroke relation tool (2) and the blade angle dispersity tool (1) respectively;
s2: the angle-stroke relation checking tool (2) and the blade angle dispersity checking tool (1) are assembled on the compressor casing (3);
s3: firstly, a second bolt (206) of the angle-stroke relation checking tool (2) is pulled out of a pin hole of a supporting seat (202), an actuating cylinder (204) is pushed, the actuating cylinder (204) moves linearly in a positioning groove of the supporting seat (202) to drive an operating rod to rotate, the second bolt (206) moves along with the actuating cylinder (204), and stroke scales of a second pressing plate (203) corresponding to the second bolt (206) are recorded;
s4: measuring the blade angle corresponding to the stroke of the actuating cylinder (204) at the moment through a blade angle dispersity inspection tool (1);
s5: pushing the actuator cylinder (204) to the rest of the stroke of the actuator cylinder (204) to be measured again, and repeating the steps S2 and S3 to obtain the installation angles of the blades corresponding to the rest of the stroke of the actuator cylinder (204).
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