CN114184390B - Gas turbine rotor axial force test sensor and parameter design method - Google Patents
Gas turbine rotor axial force test sensor and parameter design method Download PDFInfo
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- CN114184390B CN114184390B CN202210140825.8A CN202210140825A CN114184390B CN 114184390 B CN114184390 B CN 114184390B CN 202210140825 A CN202210140825 A CN 202210140825A CN 114184390 B CN114184390 B CN 114184390B
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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
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/12—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring axial thrust in a rotary shaft, e.g. of propulsion plants
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Abstract
The invention discloses a gas turbine rotor axial force test sensor and a parameter design method, wherein the gas turbine rotor axial force test sensor comprises a bearing seat, a detection ring and a temperature compensation ring, and an even number of deformation elements are uniformly distributed on the detection ring. A parameter design method comprises the following steps: according to the maximum stress on the rectangular section at any distance of the fixed support end of the force measuring beam and the maximum bending stress at the cross section of the force measuring beam; and obtaining the relation between the corner, the deflection and the maximum axial force of the free end of the force measuring beam according to the relation integral between the bending moment and the deflection of the equal-strength beam; and obtaining a parameter selection principle. The gas turbine rotor axial force test sensor and the parameter design method can effectively improve the test strain range, reduce the sensitivity of the position and direction deviation of a patch, eliminate the influence of temperature on the test result and improve the rotor axial force test precision; meanwhile, the selection of the key parameters of the rotor axial force measuring sensor can be rapidly and accurately finished.
Description
Technical Field
The invention belongs to the technical field of gas turbine rotor axial force test sensors, and particularly relates to a gas turbine rotor axial force test sensor and a parameter selection method.
Background
At present, when an axial force of an aircraft engine and a gas turbine rotor is tested, a force transducer is generally arranged on an outer ring of a bearing for direct measurement, the structural form of the transducer adopts a structure with bosses at two ends and a deformable elastic force measuring ring in the middle, the structure of the force measuring ring is shown in figure 1, axial force and strain relation calibration is carried out before a test, the strain history of the force measuring ring is tested in the test, the axial force is calculated according to the calibration relation after the test, and the transducer has the following problems in application:
1) the maximum stress is positioned at the corner of the transfer circle of the ring and the support boss, the part has serious stress concentration, and the measurable test strain of the test strain gauge is low under the condition of ensuring the rigidity and strength storage of the force transducer;
2) under the action of axial force, the force measuring ring is bent and twisted at the same time, the test surface is in a bidirectional stress state, the stress gradient is large, and the difference of the test strain of the strain gauges at different angular positions is large due to errors of the positions and directions of the strain gauge patches, so that the subsequent result analysis is not facilitated;
3) the axial load measured by the force measuring ring comprises the change of the bearing outer ring compression load caused by the axial force and the temperature of the engine, and the temperature influence is not separated in the test result.
Disclosure of Invention
The invention aims to provide a gas turbine rotor axial force test sensor and a parameter design method, and solves the problems that the existing force measuring ring has stress concentration, is in a bidirectional stress state and is not influenced by separation temperature.
In order to achieve the purpose, the invention adopts the following technical scheme:
on one hand, the invention provides a gas turbine rotor axial force test sensor which comprises a bearing seat, a detection ring and a temperature compensation ring, wherein the bearing seat is provided with a bearing outer ring, the detection ring is positioned on the side where the maximum axial force of the bearing outer ring appears, and the temperature compensation ring is positioned on the side where the axial force of the bearing outer ring can be reversed;
an even number of deformation elements are uniformly distributed on the detection ring, so that the detection ring is in a state that the stress positions are equal and the stress is unidirectional, and each deformation element is provided with a strain detection piece.
In one possible embodiment, the deformation elements are arranged on the surface of the detection ring, a plurality of deformation elements are arranged around the detection ring, and deformation gaps are left between adjacent deformation elements.
In one possible design, the deformation element comprises a sector and two force measuring beams respectively positioned at two sides of the sector, wherein the width of the sector is equal to the difference between the inner diameter and the outer diameter of the detection ring, and the central line of the force measuring beam is vertical to the end surface of the sector;
the force measuring beam is an equi-strength beam with an isosceles trapezoid longitudinal section, the lower bottom of the force measuring beam is connected to the side surface of the fan-shaped block, and the length of the lower bottom is equal to the difference between the inner diameter and the outer diameter of the detection ring;
between two adjacent deformation elements, two force-measuring beams are oppositely arranged to form a sector, and the intersection point of the two extension lines of the isosceles trapezoid waist falls on the symmetry line of the force-measuring beam of the same sector.
In one possible design, the strain detection piece is provided as a strain gauge, and correspondingly, the segment is provided with a lead slot adapted to the strain gauge;
at least two positioning grooves are also arranged on the circumference of the detection ring, and correspondingly, positioning bulges matched with the positioning grooves are arranged on the bearing seat;
one end of the force measuring beam is a fixed supporting end connected to the fan-shaped block, the other end of the force measuring beam is a free end provided with a boss, and a height difference used for limiting is arranged between the boss and the fan-shaped block.
In one possible design, the temperature compensation ring is a detection ring with the same structure and consistent radial dimension and circumferential dimension, but the axial dimension is reduced by 0.3-0.5.
In another aspect, the present invention provides a parameter design method for the gas turbine rotor axial force test sensor, including the following steps:
according to the load borne by the free end of the force measuring beam, the maximum bending stress on the rectangular section at any distance from the fixed support end of the force measuring beam is obtained;
obtaining the maximum bending stress at the cross section of the force measuring beam according to the maximum axial force and the correlation of the length, the width and the height of the fixed support end of the force measuring beam;
obtaining the relation between the free end corner, the deflection and the maximum axial force of the force measuring beam according to the relation integral between the bending moment and the deflection of the constant-strength beam;
obtaining a parameter selection principle according to a design constraint condition;
the gas turbine rotor axial force test sensor comprises a detection ring, wherein the detection ring comprises N deformation elements, each deformation element comprises a sector block and two force measurement beams respectively positioned on two sides of the sector block, one end of each force measurement beam is a fixed support end connected to the sector block, and the other end of each force measurement beam is a free end provided with a boss; the number of the force measuring beams is 2N.
In one possible design, the maximum bending stress on a rectangular cross-section (b × h) at a distance x from the load beam anchorage:
wherein, the free end of the F-force measuring beam is subjected to concentrated load; l-the length of the load beam.
In one possible design, when the force beam is an isointensity beam and the longitudinal section of the force beam is in the shape of an isosceles triangle, the stress applied to the force beam is independent of the distance x, and when the thickness h is constant, the length L and the width b should satisfy:
each deformation element corresponds to one test sector, N test sectors are arranged on the detection ring, the number of the test sectors is N, the height of the sector block is H, the central angle of the sector block is theta, the inner diameter of the detection ring is Ri, the outer diameter of the detection ring is Ro, the width of the fixed support end of the force measuring beam is not greater than (Ro-Ri), and the length of the force measuring beam is taken as follows:
width of the force beam
；
The maximum axial force is Fmax, and the load borne by the free end of each force measuring beam is
And then the maximum bending stress of the cross section of the force measuring beam is as follows:
in one possible design, the bending moment and deflection of the constant strength beam are related as follows:
the relationship between the corner, the deflection and the maximum axial force of the free end of the force measuring beam obtained by integration is as follows:
in one possible design, the design constraints are:
the load beam has sufficient yield strength reserve;
the deformation of the force measuring beam meets the requirement delta st of the axial float of the engine rotor;
the extrusion stress of the boss at the free end of the force measuring beam is not higher than 190 MPa;
boss length S1 is no greater than 25% of the beam length;
the minimum distance Ga between the free ends of adjacent force-measuring beams does not interfere when the free ends of the beams are twisted and deformed under the action of the maximum axial force;
the parameter selection principle is as follows:
has the advantages that:
the gas turbine rotor axial force test sensor and the parameter design method can eliminate stress concentration, effectively improve the test strain range, reduce the sensitivity of position and direction deviation of a patch, eliminate the influence of temperature on a test result and finally improve the rotor axial force test precision; meanwhile, the selection of the key parameters of the rotor axial force measuring sensor can be completed quickly and accurately, the design difficulty is reduced, and the design time is simplified.
Drawings
Fig. 1 is a schematic structural diagram of a conventional force measuring ring.
FIG. 2 is a schematic structural diagram of a gas turbine rotor axial force test sensor.
Fig. 3 is a schematic structural diagram of a detection ring.
Fig. 4 is a partially enlarged schematic view of the detection ring.
Fig. 5 is a schematic structural view of a section a-a in fig. 4.
Fig. 6 is a schematic structural diagram of a computer main device provided in the present invention.
In the figure:
1. a bearing seat; 101. a bearing outer ring; 2. a detection ring; 201. positioning a groove; 3. a temperature compensation loop; 4. a deformation element; 41. a sector block; 42. a force measuring beam; 401. a lead slot; 402. a boss; 403. an effective patch area; 5. a strain detection member.
Detailed Description
Example 1:
as shown in fig. 2 to 5, a gas turbine rotor axial force test sensor includes a bearing seat 1, a detection ring 2 and a temperature compensation ring 3, wherein the bearing seat 1 is provided with a bearing outer ring 101, the detection ring 2 is located on a side where a maximum axial force of the bearing outer ring 101 occurs, and the temperature compensation ring 3 is located on a side where the axial force of the bearing outer ring 101 may be reversed.
An even number of deformation elements 4 are uniformly distributed on the detection ring 2, so that the detection ring 2 is in a state that the stress positions are equal and the stress is unidirectional, and each deformation element 4 is provided with a strain detection piece 5.
The structure of the detection ring 2 is improved by the deformation element 4 arranged on the detection ring 2, so that the detection ring 2 is in the state that the stress positions are equal, at the moment, no stress concentration phenomenon exists on the detection ring 2, the measurement range of the test strain is increased under the condition of ensuring the rigidity and strength storage of the test sensor, the data collection range is improved, and the precision of the detection result is improved.
Meanwhile, the detection ring 2 can be in a one-way stress state, compared with the existing force measuring ring in a two-way stress state in the detection process, the stress gradient on the test sensor is small, and the position and direction errors of the patch of the strain detection piece 5 cause small test strain difference of the strain detection piece 5 at different angular positions, so that the subsequent analysis is facilitated, namely the sensitivity of the position and direction deviation of the patch is reduced, the operation difficulty in the detection process is reduced, and the detection speed is improved.
Wherein, the strain detection piece 5 is used for measuring the strain suffered by the test sensor, and optionally, the strain detection piece 5 can be any suitable commercially available model.
In addition, the temperature compensation ring 3 is used for eliminating the influence of temperature, specifically, before the test, the test sensor is subjected to strain and axial force calibration under different temperature and axial force conditions, after the test, the axial load processes of the detection ring 2 and the temperature compensation ring 3 are calculated according to the test strain process and the calibration result, and the difference between the axial load processes is the axial force process of the engine rotor, so that the temperature influence is separated from the test result, and the detection precision is improved.
Through the design, the gas turbine rotor axial force test sensor can eliminate stress concentration, effectively improve the test strain range, reduce the sensitivity of the position and the direction deviation of a paster, eliminate the influence of temperature on a test result, and finally improve the rotor axial force test precision.
Specifically, the operation can be divided into three stages, wherein the first stage is before the test, namely, the strain and axial force calibration is carried out on the test sensor under different temperature and axial force conditions, so that each reference value is determined. The second stage is in the test, namely the axial force of the rotor is tested by the test sensor, and various data are collected during the test. And the third stage is after the test, namely the collected data are processed, the temperature influence is eliminated simultaneously, and the axial force value of the rotor is finally obtained.
The side on which the maximum axial force occurs and the side on which the axial force may reverse will now be described: in the working process of the gas turbine, the axial force borne by the thrust bearing is the resultant force of the axial forces of the compressor rotor and the turbine rotor, the directions of the axial forces and the turbine rotor are opposite, in order to ensure that the bearing is not subjected to sliding damage caused by axial force reversing in the design, the resultant forces of the axial forces of the compressor rotor and the turbine rotor generally all follow the same direction, the direction is defined as the direction of the maximum axial force, the reverse direction of the maximum axial force is the possible reversing direction, the side pointed by the direction of the maximum axial force is the maximum axial force side of the bearing, and the opposite side of the maximum axial force side of the bearing is the possible reversing side.
Optionally, the layout form of the test sensor includes but is not limited to: the bottom surface of the bearing seat 1 is provided with a mounting groove, the bearing outer ring 101 is fixed in the mounting groove, gaps are reserved on two sides of the bearing outer ring 101, one of the two gaps is used for mounting the detection ring 2, and the other gap is used for mounting the temperature compensation ring 3.
The test is further described below with reference to the specific structure of the test sensor:
in a possible implementation, the deformation element 4 is arranged on the surface of the detection ring 2, a plurality of deformation elements 4 being arranged around the detection ring 2; that is, the deformation element 4 is disposed on the surface or the bottom surface of the detection ring 2, when the detection ring 2 is inserted into the mounting groove, the deformation element 4 abuts against the side surface of the bearing outer ring 101, and in the test, the deformation element 4 is deformed by a force and tested for strain by the strain detection member 5.
In a possible implementation, a deformation gap is left between adjacent deformation elements 4, i.e. in the experiment, the deformation elements 4 are deformed in the form of being compressed, the thickness of the deformation elements 4 is reduced, the length is increased, and the deformation gap is reserved to avoid mutual interference between two adjacent deformation elements 4 in the experiment.
In the present embodiment, the deformation element 4 comprises a sector 41 and two load beams 42 respectively located on both sides of the sector 41, wherein the width of the sector 41 is equal to the difference between the inner and outer diameters of the detection ring 2, and the center line of the load beam 42 is perpendicular to the end face of the sector 41; the force measuring beam 42 is an equal-strength beam with an isosceles trapezoid longitudinal section, the lower bottom of the force measuring beam 42 is connected to the side face of the sector block 41, and the length of the lower bottom is equal to the difference between the inner diameter and the outer diameter of the detection ring 2; between two adjacent deformation elements 4, two force measuring beams 42 are oppositely arranged and form a sector, and the intersection point of the extension lines of the two waists of the isosceles trapezoid falls on the symmetry line of the force measuring beam 42 of the same sector.
In this way, the effective patch area 403 of the detection ring 2 is under the same stress, and is in a unidirectional stress state, so that the stress concentration phenomenon is eliminated, the requirement on patch precision is reduced, the preparation work is simplified, and the efficiency is improved. The patch area refers to an area where the strain detector 5 can be attached, the effective patch area 403 is a portion of the patch area where strain can be effectively measured, and generally, the effective patch area 403 is a top surface of the load beam 42.
In one possible implementation, the strain detector 5 is provided as a strain gauge, and accordingly, the segment 41 is provided with a lead groove 401 adapted to the strain gauge; the lead groove 401 is used in cooperation with the strain gauge and used for accommodating and guiding the lead part of the strain gauge, so that the influence of the lead part on the test result is avoided, and the measurement precision is improved.
Preferably, the lead groove 401 is located on the inner circumference of the detection ring 2 and extends along the centerline of the segment 41. Alternatively, the groove shape of the lead groove 401 includes, but is not limited to, a T-shaped groove, and may be configured into any suitable shape according to the actual use situation.
In a possible implementation manner, at least two positioning grooves 201 are further arranged in the circumferential direction of the detection ring 2, and correspondingly, the bearing seat 1 is provided with positioning protrusions adapted to the positioning grooves 201; namely, the positioning groove 201 is used for quick installation, and the preparation efficiency is improved. It is easy to understand that the positioning grooves 201 are uniformly distributed on the circumference of the detection ring 2, and the number of the positioning grooves 201 includes but is not limited to two, which can be adaptively increased according to the actual use situation.
Simultaneously, the location is protruding to cooperate and is used in constant head tank 201, when detecting the installation of ring 2, rotates to detect ring 2 and makes the protruding grafting of location to the constant head tank 201 in can accomplish the installation. It is known that the detent projection can be configured in any shape that fits into the detent 201.
In a possible implementation manner, one end of the force measuring beam 42 is a fixed end connected to the sector block 41, the other end of the force measuring beam 42 is a free end provided with a boss 402, and a height difference for limiting is provided between the boss 402 and the sector block 41. Based on the above design, boss 402 and sector 41 mutually support, form limit structure on the one hand, cooperate in constant head tank 201 and use, improve the convenience of installation, and on the other hand has realized overload protection, avoids measuring force beam 42 plastic deformation to appear, influences follow-up measuring accuracy.
It will be readily appreciated that the difference in height between the boss 402 and the segment 41 is well known to those skilled in the art and will not be described further herein.
Meanwhile, the bosses 402 are located at the free ends of the load beams 42, and the deformation gap between adjacent load beams 42 is the gap between two adjacent bosses 402; alternatively, the boss 402 may be configured in any suitable shape.
Obviously, the temperature in the test will cause the compression load of the bearing outer ring 101 to change, the temperature compensation ring 3 is used for eliminating the influence, and specifically, the temperature compensation ring 3 is the detection ring 2 which has the same structure and consistent radial dimension and circumferential dimension, but the axial dimension is reduced by 0.3-0.5.
The temperature compensation ring 3 and the detection ring 2 are arranged along the same axial direction, so that the radial dimension and the circumferential dimension are consistent; the change value of the compression load caused by the temperature influence is small, so that the axial size needs to be scaled, the measurement range is further reduced, the measurement precision is increased, the test precision is further improved, and the specific axial size scaling is determined according to the reversing axial force and the pretightening force.
Example 2:
the present embodiment provides a parameter design method for a gas turbine rotor axial force test sensor in embodiment 1 on the basis of embodiment 1, and specifically, a parameter design method for the gas turbine rotor axial force test sensor includes, but is not limited to, the following steps:
s101: according to the load borne by the free end of the force measuring beam 42, the maximum bending stress on the rectangular section at any distance from the fixed end of the force measuring beam 42 is obtained;
s102: obtaining the maximum bending stress at the cross section of the force measuring beam 42 according to the maximum axial force and the correlation of the length, the width and the height of the fixed end of the force measuring beam 42;
s103: obtaining the relation between the corner, the deflection and the maximum axial force of the free end of the force measuring beam 42 according to the relation integral between the bending moment and the deflection of the equal-strength beam;
s104: and obtaining a parameter selection principle according to the design constraint condition.
The gas turbine rotor axial force test sensor comprises a test ring 2, wherein the test ring 2 comprises N deformation elements 4, each deformation element 4 comprises a sector block 41 and two force measurement beams 42 which are respectively positioned on two sides of the sector block 41, one end of each force measurement beam 42 is a fixed end connected to the sector block 41, and the other end of each force measurement beam 42 is a free end provided with a boss 402; the number of the load beams 42 is 2N.
According to the design, the selection of the key parameters of the rotor axial force measuring sensor can be quickly and accurately completed, meanwhile, the designed rotor axial force measuring sensor can effectively improve the testing strain range, reduce the sensitivity of the position and direction deviation of a patch, eliminate the influence of temperature on a testing result, and finally improve the testing precision of the rotor axial force.
Specifically, in step S101, the maximum bending stress on the rectangular cross section (b × h) at a distance x from the fixed end of the load beam 42:
wherein, the free end of the F-force measuring beam 42 bears concentrated load; l-the length of the load beam 42.
In step S102, when the load beam 42 is an equal strength beam and the shape of the longitudinal section of the load beam 42 is an isosceles triangle, the stress applied to the load beam 42 is independent of the distance x, and when the thickness h is constant, the length L and the width b should satisfy:
each deformation element 4 corresponds to one test sector, N test sectors are arranged on the detection ring 2, the number of the test sectors is N, the height of the sector block 41 is H, the central angle of the sector block 41 is theta, the inner diameter of the detection ring 2 is Ri, the outer diameter of the detection ring 2 is Ro, the width of the fixed end of the force measuring beam 42 is not greater than (Ro-Ri), and the length of the force measuring beam 42 is:
width of the load beam 42
；
The maximum axial force is Fmax, and the load on the free end of each force measuring beam 42 is
Then, the maximum bending stress of the cross section of the load beam 42 is:
in step S103, the relationship between the bending moment and the deflection of the constant-strength beam is as follows:
the relationship between the corner, the deflection and the maximum axial force of the free end of the force measuring beam obtained by integration is as follows:
in step S104, the design constraints are: the force-measuring beam 42 has enough yield strength reserve, the deformation of the force-measuring beam 42 meets the requirement delta st of the axial float of the engine rotor; the extrusion stress of the boss 402 at the free end of the force measuring beam 42 is not higher than 190 MPa; the boss 402 length S1 is no greater than 25% of the beam length; the minimum distance Ga between the free ends of the adjacent force measuring beams 42 does not interfere when the free ends of the beams are twisted and deformed under the action of the maximum axial force;
the following design parameter selection principles are given:
example 3:
as shown in fig. 6, the present embodiment provides a parameter design apparatus for a gas turbine rotor axial force test sensor, the apparatus being a computer main device, including: the parameter design method comprises a memory, a processor and a transceiver which are sequentially connected in a communication mode, wherein the memory is used for storing a computer program, the transceiver is used for transmitting and receiving messages, and the processor is used for reading the computer program and executing the parameter design method of the gas turbine rotor axial force test sensor in the embodiment 2.
For example, the memory may include, but is not limited to, a Random Access Memory (RAM), a Read Only Memory (ROM), a flash memory (FlashMemory), a first in first out memory (FIFO), and/or a first in last out memory (FILO), and the like; the processor may not be limited to a microprocessor of a model number STM32F105 series, a reduced instruction set computer (RSIC) microprocessor, an architecture processor such as X86, or a processor integrated with an embedded neural Network Processor (NPU); the transceiver may be, but is not limited to, a wireless fidelity (WiFi) wireless transceiver, a bluetooth wireless transceiver, a General Packet Radio Service (GPRS) wireless transceiver, a ZigBee wireless transceiver (a low power local area network protocol based on the ieee802.15.4 standard), a 3G transceiver, a 4G transceiver, and/or a 5G transceiver, etc. In addition, the device may also include, but is not limited to, a power module, a display screen, and other necessary components.
The working process, working details, and technical effects of the device provided in this embodiment may be referred to as embodiment 2, and are not described herein again.
The embodiment also provides a readable storage medium storing instructions for implementing the parameter design method for the axial force test sensor of the gas turbine rotor according to embodiment 2, namely, the readable storage medium stores instructions thereon, which when executed on a computer, perform the parameter design method for the axial force test sensor of the gas turbine rotor. The readable storage medium refers to a carrier for storing data, and may include, but is not limited to, a floppy disk, an optical disk, a hard disk, a flash memory, a flash disk and/or a memory stick (memory stick), etc., and the computer may be a general-purpose computer, a special-purpose computer, a computer network, or other programmable device.
The working process, working details, and technical effects of the storage medium provided in this embodiment may be referred to as embodiment 2, and are not described herein again.
The present embodiments also provide a computer program product containing instructions which, when run on a computer, which may be a general purpose computer, a special purpose computer, a computer network or other programmable device, cause the computer to perform the method of parametric design of a gas turbine rotor axial force test sensor as described.
Finally, it should be noted that: the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. The gas turbine rotor axial force test sensor is characterized by comprising a bearing seat (1), a detection ring (2) and a temperature compensation ring (3), wherein the bearing seat (1) is provided with a bearing outer ring (101), the detection ring (2) is positioned on the side where the maximum axial force of the bearing outer ring (101) occurs, and the temperature compensation ring (3) is positioned on the side where the axial force of the bearing outer ring (101) can be reversed;
an even number of deformation elements (4) are uniformly distributed on the detection ring (2) so that the detection ring (2) is in a state that stress positions are equal and the stress positions are in a one-way stress state, and each deformation element (4) is provided with a strain detection piece (5);
the deformation element (4) comprises a fan-shaped block (41) and two force measuring beams (42) which are respectively positioned on two sides of the fan-shaped block (41), wherein the width of the fan-shaped block (41) is equal to the difference between the inner diameter and the outer diameter of the detection ring (2), and the central line of the force measuring beam (42) is vertical to the end surface of the fan-shaped block (41);
the force measuring beam (42) is an equi-strength beam with an isosceles trapezoid longitudinal section, the lower bottom of the force measuring beam (42) is connected to the side surface of the fan-shaped block (41), and the length of the lower bottom is equal to the difference between the inner diameter and the outer diameter of the detection ring (2);
between two adjacent deformation elements (4), two force measuring beams (42) are oppositely arranged to form a sector, and the intersection point of the extension lines of the two waists of the isosceles trapezoid falls on the symmetry line of the force measuring beam (42) of the same sector.
2. Gas turbine rotor axial force test sensor according to claim 1, characterized in that the deformation elements (4) are arranged on the surface of the detection ring (2), a plurality of deformation elements (4) are arranged around the detection ring (2), and deformation gaps are left between adjacent deformation elements (4).
3. The gas turbine rotor axial force test sensor according to claim 1, characterized in that the strain detecting member (5) is provided as a strain gauge, and correspondingly, a lead groove (401) adapted to the strain gauge is provided on the segment (41);
the circumference of the detection ring (2) is also provided with at least two positioning grooves (201), and correspondingly, the bearing seat (1) is provided with positioning bulges which are matched with the positioning grooves (201);
one end of the force measuring beam (42) is a fixed support end connected to the sector block (41), the other end of the force measuring beam (42) is a free end provided with a boss (402), and a height difference used for limiting is arranged between the boss (402) and the sector block (41).
4. The gas turbine rotor axial force test sensor according to claim 3, characterized in that the temperature compensation ring (3) is a detection ring (2) with the same structure and the same radial dimension and circumferential dimension, but the axial dimension is reduced by 0.3-0.5.
5. A parametric design method for a gas turbine rotor axial force test sensor according to any one of claims 1 to 4, comprising the steps of:
according to the load borne by the free end of the force measuring beam (42), the maximum bending stress on the rectangular section at any distance from the fixed end of the force measuring beam (42) is obtained;
obtaining the maximum bending stress at the cross section of the force measuring beam (42) according to the maximum axial force and the correlation of the length, the width and the height of the fixed support end of the force measuring beam (42);
obtaining the relation between the corner, the deflection and the maximum axial force of the free end of the force measuring beam (42) according to the relation integral between the bending moment and the deflection of the equal-strength beam;
obtaining a parameter selection principle according to a design constraint condition;
the gas turbine rotor axial force test sensor comprises a detection ring (2), wherein the detection ring (2) comprises N deformation elements (4), each deformation element (4) comprises a fan-shaped block (41) and two force measurement beams (42) which are respectively positioned on two sides of the fan-shaped block (41), one end of each force measurement beam (42) is a fixed support end connected to the fan-shaped block (41), and the other end of each force measurement beam (42) is a free end provided with a boss (402); the number of the force measuring beams (42) is 2N.
6. Parameter design method according to claim 5, characterized in that the maximum bending stress on a rectangular cross section (b x h) at a distance x from the anchorage end of the load beam (42):
wherein, the free end of the F-force measuring beam (42) bears concentrated load; l-the length of the load beam (42).
7. Parameter design method according to claim 6, characterized in that, when the load beam (42) is an isointensity beam and the longitudinal cross-sectional shape of the load beam (42) is an isosceles triangle, the load beam (42) is stressed independently of the distance x, and when the thickness h is constant, the length L and the width b are such that:
each deformation element (4) corresponds to a test sector, and N test sectors are arranged on the detection ring (2) for testingThe number of sectors is N, the height of the sector (41) is H, the central angle of the sector (41) is theta, the inner diameter of the detection ring (2) is Ri, the outer diameter of the detection ring (2) is Ro, the width of the fixed end of the force measuring beam (42) is not greater than (Ro-Ri), and the length of the force measuring beam (42) is as follows:
width of the load beam (42)
；
The maximum axial force is Fmax, and the load borne by the free end of each force measuring beam (42) is
And then the maximum bending stress of the cross section of the force measuring beam (42) is as follows:
8. the parametric design method of claim 7, wherein the bending moment and the deflection of the constant-strength beam are related as follows:
the relation of the free end corner, the deflection and the maximum axial force of the force measuring beam (42) obtained by integration is as follows:
9. the parametric design method of claim 8, wherein the design constraints are:
the load beam (42) has a sufficient yield strength reserve;
the deformation of the force measuring beam (42) meets the requirement delta st of the axial float of the engine rotor;
the extrusion stress of a boss (402) at the free end of the force measuring beam (42) is not higher than 190 MPa;
the boss (402) length S1 is no greater than 25% of the beam length;
the minimum distance Ga between the free ends of adjacent force-measuring beams (42) does not interfere when the free ends of the beams are twisted and deformed under the action of the maximum axial force;
the parameter selection principle is as follows:
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| CN115270285B (en) * | 2022-06-07 | 2023-08-04 | 中国航发沈阳发动机研究所 | Method for determining design requirements of axial force of aero-engine rotor |
| CN116384010B (en) * | 2023-06-01 | 2023-09-01 | 中国航发四川燃气涡轮研究院 | Engine bench fan rotor axial force evaluation method capable of being corrected in real time |
| CN116951184B (en) * | 2023-09-20 | 2023-12-26 | 成都中科翼能科技有限公司 | Test pipeline sealing structure of gas turbine |
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