CN106837426A - A kind of eccentric optimization method of engine core machine rotor barycenter - Google Patents
A kind of eccentric optimization method of engine core machine rotor barycenter Download PDFInfo
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- CN106837426A CN106837426A CN201710084586.8A CN201710084586A CN106837426A CN 106837426 A CN106837426 A CN 106837426A CN 201710084586 A CN201710084586 A CN 201710084586A CN 106837426 A CN106837426 A CN 106837426A
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/10—Anti- vibration means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
Abstract
The invention discloses the optimization method that a kind of engine core machine rotor barycenter is eccentric.The eccentric optimization method of the engine core machine rotor barycenter is comprised the following steps：Step 1：Using the minimum value of core machine rotor joint face centre of form bias OC as the eccentric optimization method of the engine core machine rotor barycenter optimization aim；Step 2：Set up core engine rotor centroid bias prediction optimization Mathematical Modeling；Step 3：Corresponding θ values when labyrinth fitting centre of form O deviates core machine rotor actual rotation axis OC minimums are obtained, High Pressure Turbine Rotor is carried out according to the θ values and the angular rotating dress of high-pressure compressor rotor is matched somebody with somebody.The eccentric optimization method of the engine core machine rotor barycenter of the application is before rotor assembling, corresponding angular phasing instructs core engine rotor to assemble when calculating selection OC value minimums by optimizing, and then realize reducing core engine rotor centroid bias, reduce core engine rotor unbalance value, improve the purpose of high pressure rotor vibration.
Description
Technical field
The present invention relates to aero-engine technology field, more particularly to a kind of engine core machine rotor barycenter bias
Optimization method.
Background technology
Core Engine rotor unbalance value is the key factor for determining engine rotor vibratory response, and is produced
The basic reason of amount of unbalance is that each discrete rotor centroid deviate from actual rotation axis.Certain core machine rotor is by having balanced
High-pressure compressor rotor (HPC) and High Pressure Turbine Rotor (HPT) are assembled by self-locking screw/nut.It is computed, when the core
It is 0.01mm that machine rotor barycenter is eccentric, when rotating speed is 12000r/min, can produce the centrifugal force of about 400kg, the order of magnitude from
Mental and physical efforts will break the poised state of rotor, and then cause high pressure rotor to vibrate.
Reference picture 1, in theory, the barycenter distribution of high-pressure compressor rotor is fitted centre of form A and comb tooth in preceding axle journal after balance
On the line AO of disk fitting centre of form O, the barycenter distribution of High Pressure Turbine Rotor is fitted centre of form O in labyrinth and rear shaft neck is intended after balance
Close on the line OB of centre of form B.Therefore, high-pressure compressor rotor and High Pressure Turbine Rotor are being assembled into the process of core machine rotor
In, the value OC for taking effective process control labyrinth fitting centre of form O to deviate actual rotation axis AB is as small as possible, can drop
Low core engine rotor centroid is eccentric, reduces the size of rotor unbalance value, improves the distribution of amount of unbalance, and effectively reduces high pressure
Rotor oscillation is transfinited the frequency of generation.
For the core machine rotor of the structure type, existing core machine rotor assembly technology mainly has following two schemes：
(1) assembling principle is offset in bounce.I.e. under band model rotor poised state, compressor rotor is measured respectively and whirling high is corresponding
The bounce of cylinder, assemble rotor after the two highest bounce point is exchanged into 180 °.(2) amount of unbalance offsets assembling principle.I.e. two
Rotor is balanced respectively, and most amount of unbalance measurement phase exchanges assemble rotor after 180 degree at last.Filled using both the above method
After with complete core machine rotor, the value for being both needed to using special measuring tool measurement OC (circumferentially install side and fix, energy mould by measuring tool and stator casing
Intend actual rotary shaft AB), and be controlled this as important technical parameter, if OC is overproof, need to divide by by two high pressure rotors
The mode of solution-rotatable phase-trial assembly is reassembled.
Above core machine rotor assembly technology is although feasible, but to the poor controllability of key process parameter OC values, easily causes
During biography dress because of the overproof assembling for causing of OC repetition measurements repeatedly, and because of the eccentric excessive caused high pressure vibration of core engine rotor centroid
Also happen occasionally, cause efficiency of assembling low, the manufacturing cost of engine is improve indirectly, and there is technique to parts existing structure
Inherent vibration performance excavate it is not in place the problems such as.
Thus, it is desirable to have a kind of technical scheme come overcome or at least mitigate prior art at least one drawbacks described above.
The content of the invention
Overcome it is an object of the invention to provide a kind of eccentric optimization method of engine core machine rotor barycenter or extremely
Mitigate at least one drawbacks described above of prior art less.
To achieve the above object, the present invention provides a kind of engine core machine rotor barycenter eccentric optimization method, described
The eccentric optimization method of engine core machine rotor barycenter is comprised the following steps：
Step 1：After high-pressure compressor rotor and High Pressure Turbine Rotor are obtained with the assembling of any anglec of rotation phase theta, rear shaft neck
The cylinder at place is eccentric, and then obtains the value of BE；
Step 2：Before the assembling of core machine rotor, keep high-pressure compressor rotor motionless, single direction rotation High Pressure Turbine Rotor,
And the angular step value θ of rotation is the integer multiple of 360 °/n, wherein, n is joint face coupling bar number, and 9 grades of combs are obtained one by one
Seam cylinder is fitted actual rotation axis AB that centre of form O constituted to front and rear fulcrum line apart from OC after fluted disc, and by the OC most
Small probable value as the eccentric optimization method of the engine core machine rotor barycenter optimization aim；
Step 3：Set up core engine rotor centroid bias prediction optimization Mathematical Modeling；
Step 4：Core engine rotor centroid bias prediction optimization Mathematical Modeling according to the step 3 obtains labyrinth fitting
Corresponding θ values when centre of form O bias OC is minimum, carry out High Pressure Turbine Rotor and high-pressure compressor rotor angularly rotate according to the θ values
Assembling.
Preferably, the step 1 is specifically included：
Step 11：Obtain front fulcrum section and be fitted the centre of form to 9 grades of labyrinths and the axle of the corresponding end face of drum barrel axle cooperation seam
To length AD；
Step 12：Obtain the axial direction that fulcrum section is fitted centre of form B to 9 grades of labyrinth end face corresponding with drum barrel axle cooperation seam
Length DE；
Step 13：Measurement high-pressure compressor rotor component jitter parameter；
Step 14：Measurement High Pressure Turbine Rotor jitter parameter；
Step 15：After acquisition compressor rotor component and the assembling of High Pressure Turbine Rotor component at core machine rotor rear shaft neck
Comprehensive eccentricity equations；
Step 16：It is input with the parameter that step 11 to step 14 is obtained, by the comprehensive eccentricity equations of step 15, calculates
After compressor rotor and High Pressure Turbine Rotor are obtained with the assembling of any anglec of rotation phase theta, the cylinder at rear shaft neck is eccentric.
Preferably, the step 13 is specially：In stacking optimization equipment, with axle journal before high-pressure compressor rotor component
Install on the basis of the cylinder S and shaft shoulder end face T at front fulcrum bearing inner ring, 9 grades of labyrinths of measurement coordinate seam with drum barrel axle
Cylinder bias δcenter1With the end face eccentric δ that 9 grades of labyrinths and drum barrel axle coordinate seamtlit。
Preferably, the step 14 is specially：In stacking optimization equipment, with High Pressure Turbine Rotor component drum barrel axle and 9
Level labyrinth coordinates on the basis of the corresponding cylinder S and end face T of seam, and the post at rear fulcrum outer race is installed in measurement rear shaft neck
Face bias δcenter3。
Preferably, the comprehensive eccentricity equations in the step 15 are specially：
Wherein,
δcenterIt is the comprehensive bias of rear shaft neck bearing pivot on the basis of core machine rotor front axle neck；
δcenter1On the basis of former axle journal, 9 grades of labyrinths coordinate the cylinder of seam eccentric with drum barrel axle；
δcenter2=H* δtilt/ (D/2), δcenter2For nine grades of labyrinth rear end faces of high-pressure compressor incline δtiltTo core
The eccentric influence of machine rear shaft neck cylinder；
H is axial dimension of the High Pressure Turbine Rotor drum barrel axle front end face to rear shaft neck bearing pivot；
D is the cooperation cylinder diameter dimension of seam after nine grades of labyrinths of high-pressure compressor；
δtlitOn the basis of former axle journal, 9 grades of labyrinths coordinate the end face eccentric of seam with drum barrel axle；
δcenter3It is that on the basis of seam before drum barrel axle, the cylinder at High Pressure Turbine Rotor component rear shaft neck is eccentric.
Preferably, the step 16 is specially：With seam cylinder bias δ after labyrinthcenter1, seam end face after labyrinth
Eccentric δtlitThe rear fulcrum outer race cylinder bias δ measured with step 14center3It is input, can be by being calculated compressor
After rotor and High Pressure Turbine Rotor are assembled with any anglec of rotation phase theta, the cylinder at rear shaft neck is eccentric.
Preferably, the core engine rotor centroid bias prediction optimization Mathematical Modeling in the step 3 is：Wherein,
CD：CD=BE*AD/ (AD+DE) is similar to △ ABE according to △ ACD；
BE：Core machine rotor rear fulcrum cylinder in the past on the basis of axle journal is eccentric, can be tried to achieve according to the method for step 1；
AD：High-pressure compressor rotor front axle cervical branch o'clock, can be according to step 11 to 9 grades of axial dimensions of labyrinth rear end face
Method is tried to achieve；
DE：High Pressure Turbine Rotor drum barrel axle front end face, can be according to the method for step 12 to the axial dimension of rear shaft neck fulcrum
Try to achieve；
θ is the angular step value that High Pressure Turbine Rotor relatively high pressure compressor rotor rotating dress is matched somebody with somebody.
The eccentric optimization method of the engine core machine rotor barycenter of the application calculates choosing before rotor assembling by optimizing
Selecting the minimum angular phasing of OC values instructs core engine rotor to assemble, and realizes that reduction core engine rotor centroid is eccentric indirectly, reduces core
Machine rotor amount of unbalance, improves the purpose of high pressure rotor vibration.
The method achieve seam fitting centre of form bias after core machine rotor labyrinth is optimized before assembly, indirectly
Control rotor centroid is eccentric, improves an assembly yield, reduces assembling manufacturing cost；
The method can be excavated and had in parts in the maximum of vibration performance, reduce and improve high pressure rotor vibration；
Repetition measurement after assembling can be omitted with the maturation of the method application, in technique, development cost is effectively reduced.
Brief description of the drawings
Fig. 1 is the existing structural representation using the engine core machine rotor of repetition measurement technology after assembling.
Fig. 2 is the schematic flow sheet of the optimization method of the engine core machine rotor barycenter bias of the embodiment of the application one.
Fig. 3 is the compressor rotor component bounce of the optimization method of the engine core machine rotor barycenter bias shown in Fig. 2
Parameter measurement schematic diagram.
Fig. 4 is that the High Pressure Turbine Rotor component of the optimization method of the engine core machine rotor barycenter bias shown in Fig. 2 is jumped
Dynamic parameter measurement schematic diagram.
Fig. 5 is that the rotor nonconcentricity superposition of the optimization method of the engine core machine rotor barycenter bias shown in Fig. 2 is former
The schematic diagram of reason.
Fig. 6 is that the rotor nonconcentricity superposition of the optimization method of the engine core machine rotor barycenter bias shown in Fig. 2 is former
Another schematic diagram of reason.
Fig. 7 is that the core engine rotor centroid of the optimization method of the engine core machine rotor barycenter bias shown in Fig. 2 is eccentric
The schematic diagram of prediction optimization Mathematical Modeling.
Reference：
| 1 | High-pressure compressor rotor | 6 | Rear fulcrum installation site |
| 2 | High Pressure Turbine Rotor | 7 | Rear shaft neck |
| 3 | 9 grades of labyrinths | 8 | Whirlpool disk high |
| 4 | Front fulcrum installation site | 9 | Drum barrel axle |
| 5 | Preceding axle journal |
Specific embodiment
To make the purpose, technical scheme and advantage of present invention implementation clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.Embodiment below with reference to Description of Drawings is exemplary, it is intended to used
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Face is described in detail with reference to accompanying drawing to embodiments of the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outward " are based on accompanying drawing institute
The orientation or position relationship for showing, are for only for ease of the description present invention and simplify description, rather than the dress for indicating or implying meaning
Put or element with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that must be protected to the present invention
The limitation of scope.
Fig. 2 is the schematic flow sheet of the optimization method of the engine core machine rotor barycenter bias of the embodiment of the application one.
Fig. 3 is the compressor rotor component jitter parameter measurement of the optimization method of the engine core machine rotor barycenter bias shown in Fig. 2
Schematic diagram.Fig. 4 is the High Pressure Turbine Rotor component bounce of the optimization method of the engine core machine rotor barycenter bias shown in Fig. 2
Parameter measurement schematic diagram.Fig. 5 is the rotor nonconcentricity of the optimization method of the engine core machine rotor barycenter bias shown in Fig. 2
The schematic diagram of principle of stacking.Fig. 6 is the rotor decentraction of the optimization method of the engine core machine rotor barycenter bias shown in Fig. 2
Spend another schematic diagram of principle of stacking.Fig. 7 is the core of the optimization method of the engine core machine rotor barycenter bias shown in Fig. 2
The schematic diagram of machine rotor barycenter bias prediction optimization Mathematical Modeling.
The eccentric optimization method of engine core machine rotor barycenter as shown in Figure 2 is comprised the following steps：
Step 1：After compressor rotor and High Pressure Turbine Rotor are obtained with the assembling of any anglec of rotation phase theta, at rear shaft neck
Cylinder is eccentric, and then obtains the value of BE；
Step 2：Before the assembling of core machine rotor, keep compressor rotor motionless, single direction rotation High Pressure Turbine Rotor, and rotation
The angular step value θ for turning is the integer multiple of 360 °/n, wherein, n is joint face coupling bar number, and 9 grades of labyrinths are obtained one by one
Seam cylinder is fitted actual rotation axis AB that centre of form O constituted to front and rear fulcrum line apart from OC afterwards, and by the most I of the OC
The optimization aim as the eccentric optimization method of the engine core machine rotor barycenter can be worth；
Step 3：Set up core engine rotor centroid bias prediction optimization Mathematical Modeling；
Step 4：Core engine rotor centroid bias prediction optimization Mathematical Modeling according to the step 3 obtains labyrinth fitting
Corresponding θ values when centre of form O bias OC is minimum, carry out High Pressure Turbine Rotor and high-pressure compressor rotor angularly rotate according to the θ values
Assembling.
In the present embodiment, step 1 is specifically included：Step 11：Obtain front fulcrum section be fitted the centre of form to 9 grades of labyrinths with
Drum barrel axle coordinates the axial length AD of seam correspondence end face；Specifically, can be by checking that the high-pressure compressor that design is provided turns
Sub-component figure, checkpoint front fulcrum section is fitted the axial length of centre of form A to 9 grades of labyrinth end face corresponding with drum barrel axle cooperation seam
AD。
Step 12：Obtain the axial direction that fulcrum section is fitted centre of form B to 9 grades of labyrinth end face corresponding with drum barrel axle cooperation seam
Length DE；Can be by checking the High Pressure Turbine Rotor component drawings that design is provided, checkpoint rear fulcrum section is fitted centre of form B to 9 grades
The axial length DE of labyrinth end face corresponding with drum barrel axle cooperation seam.
Step 13：Measurement high-pressure compressor rotor component jitter parameter；Reference picture 3, in stacking optimization equipment, with high pressure
(correspondence reference axis on the basis of cylinder S and shaft shoulder end face T at front fulcrum bearing inner ring is installed before compressor rotor component on axle journal
It is the AE of the AD and Fig. 7 of Fig. 3), 9 grades of labyrinths of measurement coordinate the cylinder bias δ of seam with drum barrel axlecenter1And end face eccentric
δtlit。
Step 14：Measurement High Pressure Turbine Rotor jitter parameter；Reference picture 4, in stacking optimization equipment, is turned with high-pressure turbine
(corresponding reference axis is in Fig. 4 on the basis of sub-component drum barrel axle coordinates the corresponding cylinder S and end face T of seam with 9 grades of labyrinths
MN, it is parallel with the DE in Fig. 7), the cylinder bias δ at rear fulcrum outer race is installed in measurement rear shaft neckcenter3。
Step 15：Obtain comprehensive eccentricity equations；Reference picture 5 and Fig. 6, the eccentric δ of Part I part1center1To second
Part part2 eccentric influence size is δcenter1, angular phasing is consistent；It is similar according to triangle, the end face of Part I part1
Eccentric δtiltIt is δ to Part II part2 eccentric influence sizecenter2=H* δ tilt/ (D/2), angular phasing biases 180 °；And
The eccentric δ of part 2center3Size and phase to itself Influence from Eccentric is constant.
Step 16：It is input with the parameter that step 11 to step 15 is obtained, by being calculated compressor rotor and high pressure
After turbine rotor is assembled with any anglec of rotation phase theta, the cylinder at rear shaft neck is eccentric.
In the present embodiment, the step 3 is specially：In stacking optimization equipment, before high-pressure compressor rotor component
Installed on axle journal on the basis of the cylinder S and shaft shoulder end face T at front fulcrum bearing inner ring, 9 grades of labyrinths of measurement coordinate with drum barrel axle
The cylinder bias δ of seamcenter1With the end face eccentric δ that 9 grades of labyrinths and drum barrel axle coordinate seamtlit。
In the present embodiment, the step 14 is specially：In stacking optimization equipment, with High Pressure Turbine Rotor component drum barrel
Axle and 9 grades of labyrinths coordinate on the basis of the corresponding cylinder S and end face T of seam, and rear fulcrum outer race is installed in measurement rear shaft neck
The cylinder bias δ at placecenter3。
In the present embodiment, the comprehensive eccentricity equations in the step 15 are specially：Its
In,
δcenterIt is the comprehensive bias of rear shaft neck bearing pivot on the basis of core machine rotor front axle neck；
δcenter1On the basis of former axle journal, 9 grades of labyrinths coordinate the cylinder of seam eccentric with drum barrel axle；
δcenter2=H* δtilt/ (D/2), δcenter2For nine grades of labyrinth rear end faces of high-pressure compressor incline δtiltTo core
The eccentric influence of machine rear shaft neck cylinder；
H is axial dimension of the High Pressure Turbine Rotor drum barrel axle front end face to rear shaft neck bearing pivot；
D is the cooperation cylinder diameter dimension of seam after nine grades of labyrinths of high-pressure compressor；
δtlitOn the basis of former axle journal, 9 grades of labyrinths coordinate the end face eccentric of seam with drum barrel axle；
δcenter3It is that on the basis of seam before drum barrel axle, the cylinder at High Pressure Turbine Rotor component rear shaft neck is eccentric.
In the present embodiment, the step 16 is specially：With seam cylinder bias δ after labyrinthcenter1, after labyrinth only
Mouth end face eccentric δtlitThe rear fulcrum outer race cylinder bias δ measured with step 14center3It is input, can be by being calculated
After compressor rotor and High Pressure Turbine Rotor are assembled with any anglec of rotation phase theta, the cylinder at rear shaft neck is eccentric.
Referring to Fig. 7, in the present embodiment, the core engine rotor centroid bias prediction optimization Mathematical Modeling in institute's step 3 is：Wherein,
CD：CD=BE*AD/ (AD+DE) is similar to △ ABE according to △ ACD；
BE：Core machine rotor rear fulcrum cylinder in the past on the basis of axle journal is eccentric, can be tried to achieve according to the method for step 1；
AD：High-pressure compressor rotor front axle cervical branch o'clock, can be according to step 11 to 9 grades of axial dimensions of labyrinth rear end face
Method is tried to achieve；
DE：High Pressure Turbine Rotor drum barrel axle front end face, can be according to the method for step 12 to the axial dimension of rear shaft neck fulcrum
Try to achieve；
θ is the angular step value that High Pressure Turbine Rotor relatively high pressure compressor rotor rotating dress is matched somebody with somebody.
The eccentric optimization method of the engine core machine rotor barycenter of the application calculates choosing before rotor assembling by optimizing
Selecting the minimum angular phasing of OC values instructs core engine rotor to assemble, and realizes that reduction core engine rotor centroid is eccentric indirectly, reduces core
Machine rotor amount of unbalance, improves the purpose of high pressure rotor vibration.
The method achieve seam fitting centre of form bias after core machine rotor labyrinth is optimized before assembly, indirectly
Control rotor centroid is eccentric, improves an assembly yield, reduces assembling manufacturing cost；
The method can be excavated and had in parts in the maximum of vibration performance, reduce and improve high pressure rotor vibration；
Repetition measurement after assembling can be omitted with the maturation of the method application, in technique, development cost is effectively reduced.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Pipe has been described in detail to the present invention with reference to the foregoing embodiments, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, do not make the essence of the essence disengaging various embodiments of the present invention technical scheme of appropriate technical solution
God and scope.
Claims (7)
1. a kind of eccentric optimization method of engine core machine rotor barycenter, it is characterised in that the engine core machine rotor
The eccentric optimization method of barycenter is comprised the following steps：
Step 1：After high-pressure compressor rotor and High Pressure Turbine Rotor are obtained with the assembling of any anglec of rotation phase theta, at rear shaft neck
Cylinder is eccentric, and then obtains the value of BE；
Step 2：Before the assembling of core machine rotor, keep high-pressure compressor rotor motionless, single direction rotation High Pressure Turbine Rotor, and rotation
The angular step value θ for turning is the integer multiple of 360 °/n, wherein, n is joint face coupling bar number, and 9 grades of labyrinths are obtained one by one
Seam cylinder is fitted actual rotation axis AB that centre of form O constituted to front and rear fulcrum line apart from OC afterwards, and by the most I of the OC
The optimization aim as the eccentric optimization method of the engine core machine rotor barycenter can be worth；
Step 3：Set up core engine rotor centroid bias prediction optimization Mathematical Modeling；
Step 4：Core engine rotor centroid bias prediction optimization Mathematical Modeling according to the step 3 obtains the labyrinth fitting centre of form
Corresponding θ values when O bias OC is minimum, carry out High Pressure Turbine Rotor and the angular rotating dress of high-pressure compressor rotor are matched somebody with somebody according to the θ values.
2. the eccentric optimization method of engine core machine rotor barycenter as claimed in claim 1, it is characterised in that the step
1 specifically includes：
Step 11：Obtain front fulcrum section and be fitted the axial length that the centre of form coordinates the corresponding end face of seam to 9 grades of labyrinths and drum barrel axle
Degree AD；
Step 12：Obtain the axial length that fulcrum section is fitted centre of form B to 9 grades of labyrinth end face corresponding with drum barrel axle cooperation seam
DE；
Step 13：Measurement high-pressure compressor rotor component jitter parameter；
Step 14：Measurement High Pressure Turbine Rotor jitter parameter；
Step 15：Obtain the synthesis at core machine rotor rear shaft neck after compressor rotor component is assembled with High Pressure Turbine Rotor component
Eccentricity equations；
Step 16：It is input with the parameter that step 11 to step 14 is obtained, by the comprehensive eccentricity equations of step 15, is calculated
After compressor rotor and High Pressure Turbine Rotor are assembled with any anglec of rotation phase theta, the cylinder at rear shaft neck is eccentric.
3. the eccentric optimization method of engine core machine rotor barycenter as claimed in claim 2, it is characterised in that the step
13 are specially：In stacking optimization equipment, installed at front fulcrum bearing inner ring with axle journal before high-pressure compressor rotor component
On the basis of cylinder S and shaft shoulder end face T, 9 grades of labyrinths of measurement coordinate the cylinder bias δ of seam with drum barrel axlecenter1With 9 grades of comb teeth
Disk coordinates the end face eccentric δ of seam with drum barrel axletlit。
4. the eccentric optimization method of engine core machine rotor barycenter as claimed in claim 3, it is characterised in that the step
14 are specially：In stacking optimization equipment, with High Pressure Turbine Rotor component drum barrel axle post corresponding with 9 grades of labyrinths cooperation seam
On the basis of face S and end face T, the cylinder bias δ at rear fulcrum outer race is installed in measurement rear shaft neckcenter3。
5. the eccentric optimization method of engine core machine rotor barycenter as claimed in claim 4, it is characterised in that the step
Comprehensive eccentricity equations in 15 are specially：
Wherein,
δcenterIt is the comprehensive bias of rear shaft neck bearing pivot on the basis of core machine rotor front axle neck；
δcenter1On the basis of former axle journal, 9 grades of labyrinths coordinate the cylinder of seam eccentric with drum barrel axle；
δcenter2=H* δtilt/ (D/2), δcenter2For nine grades of labyrinth rear end faces of high-pressure compressor incline δtiltTo core engine rear axle
The eccentric influence of neck cylinder；
H is axial dimension of the High Pressure Turbine Rotor drum barrel axle front end face to rear shaft neck bearing pivot；
D is the cooperation cylinder diameter dimension of seam after nine grades of labyrinths of high-pressure compressor；
δtlitOn the basis of former axle journal, 9 grades of labyrinths coordinate the end face eccentric of seam with drum barrel axle；
δcenter3It is that on the basis of seam before drum barrel axle, the cylinder at High Pressure Turbine Rotor component rear shaft neck is eccentric.
6. the eccentric optimization method of engine core machine rotor barycenter as claimed in claim 5, it is characterised in that the step
16 are specially：With seam cylinder bias δ after labyrinthcenter1, seam end face eccentric δ after labyrinthtlitAfter being measured with step 14
The outer circular cylinder bias δ of fulcrum rollercenter3It is input, can be by being calculated compressor rotor and High Pressure Turbine Rotor with any
After the assembling of anglec of rotation phase theta, the cylinder at rear shaft neck is eccentric.
7. the eccentric optimization method of engine core machine rotor barycenter as claimed in claim 1, it is characterised in that the step
In 3 core engine rotor centroid bias prediction optimization Mathematical Modeling be：
Wherein,
CD：CD=BE*AD/ (AD+DE) is similar to △ ABE according to △ ACD；
BE：Core machine rotor rear fulcrum cylinder in the past on the basis of axle journal is eccentric, can be tried to achieve according to the method for step 1；
AD：High-pressure compressor rotor front axle cervical branch o'clock, can be according to the method for step 11 to 9 grades of axial dimensions of labyrinth rear end face
Try to achieve；
DE：High Pressure Turbine Rotor drum barrel axle front end face can be tried to achieve to the axial dimension of rear shaft neck fulcrum according to the method for step 12；
θ is the angular step value that High Pressure Turbine Rotor relatively high pressure compressor rotor rotating dress is matched somebody with somebody.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109117461A (en) * | 2018-09-12 | 2019-01-01 | 大连理工大学 | A method of survey calculation rotor is jumped based on diameter and assembles eccentric axis |
| CN110595690A (en) * | 2019-01-07 | 2019-12-20 | 哈尔滨工业大学 | Large-scale high-speed rotation equipment measurement and intelligent learning assembly method and device based on centroid, gravity center and inertia center vector minimization |
| CN112307426A (en) * | 2020-12-28 | 2021-02-02 | 中国航发上海商用航空发动机制造有限责任公司 | Method and system for determining rotation axis |
| CN114858123A (en) * | 2021-02-04 | 2022-08-05 | 中国航发商用航空发动机有限责任公司 | Method and device for determining the concentricity of a toothed disc core relative to a rotation axis |
| CN115790976A (en) * | 2023-02-07 | 2023-03-14 | 西安航天精密机电研究所 | Method for testing working stability of H-shaped dynamic pressure motor of high-precision gyroscope |
| CN115826407A (en) * | 2022-11-29 | 2023-03-21 | 中国航发沈阳发动机研究所 | Control method for reducing rotation inertia excitation of drum shaft |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109117461A (en) * | 2018-09-12 | 2019-01-01 | 大连理工大学 | A method of survey calculation rotor is jumped based on diameter and assembles eccentric axis |
| CN110595690A (en) * | 2019-01-07 | 2019-12-20 | 哈尔滨工业大学 | Large-scale high-speed rotation equipment measurement and intelligent learning assembly method and device based on centroid, gravity center and inertia center vector minimization |
| CN112307426A (en) * | 2020-12-28 | 2021-02-02 | 中国航发上海商用航空发动机制造有限责任公司 | Method and system for determining rotation axis |
| CN112307426B (en) * | 2020-12-28 | 2021-03-26 | 中国航发上海商用航空发动机制造有限责任公司 | Method and system for determining rotation axis |
| CN114858123A (en) * | 2021-02-04 | 2022-08-05 | 中国航发商用航空发动机有限责任公司 | Method and device for determining the concentricity of a toothed disc core relative to a rotation axis |
| CN114858123B (en) * | 2021-02-04 | 2023-08-11 | 中国航发商用航空发动机有限责任公司 | Method and device for determining concentricity of center of comb plate disk relative to rotation axis |
| CN115826407A (en) * | 2022-11-29 | 2023-03-21 | 中国航发沈阳发动机研究所 | Control method for reducing rotation inertia excitation of drum shaft |
| CN115826407B (en) * | 2022-11-29 | 2024-04-09 | 中国航发沈阳发动机研究所 | Control method for reducing drum shaft rotation inertia excitation |
| CN115790976A (en) * | 2023-02-07 | 2023-03-14 | 西安航天精密机电研究所 | Method for testing working stability of H-shaped dynamic pressure motor of high-precision gyroscope |
| CN115790976B (en) * | 2023-02-07 | 2023-04-14 | 西安航天精密机电研究所 | Method for testing working stability of H-shaped dynamic pressure motor of high-precision gyroscope |
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