CN105736059B - High-speed dynamic balance ability optimization design method for gas turbine pull rod rotor with end face teeth - Google Patents

High-speed dynamic balance ability optimization design method for gas turbine pull rod rotor with end face teeth Download PDF

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CN105736059B
CN105736059B CN201610069281.5A CN201610069281A CN105736059B CN 105736059 B CN105736059 B CN 105736059B CN 201610069281 A CN201610069281 A CN 201610069281A CN 105736059 B CN105736059 B CN 105736059B
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rotor
gas turbine
unbalance
optimization
pull rod
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CN105736059A (en
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袁奇
刘洋
陈谦
王梦瑶
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Xian Jiaotong University
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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
    • F01D5/027—Arrangements for balancing
    • 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
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06N—COMPUTING ARRANGEMENTS BASED ON SPECIFIC COMPUTATIONAL MODELS
    • G06N3/00—Computing arrangements based on biological models
    • G06N3/12—Computing arrangements based on biological models using genetic models
    • G06N3/126—Evolutionary algorithms, e.g. genetic algorithms or genetic programming

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Abstract

The invention discloses a high-speed dynamic balance ability optimization design method for a gas turbine pull rod rotor with end face teeth. The high-speed dynamic balance ability optimization design method is used for optimizing the high-speed dynamic balance ability of the gas turbine pull rod rotor. According to the method, an objective function for optimizing the installation angles of wheel discs of the gas turbine rotor is provided, the installation angles of the wheel discs are optimized through the genetic algorithm, the unbalance centrifugal force on the gas turbine rotor and the bending moment exerted on the midpoint of the rotor by the unbalance centrifugal force are lowered, the multi-objective genetic algorithm is adopted for optimizing the installation angles of the wheel discs of the gas turbine rotor, the unbalance response amplitude of the rotor is obviously lowered after optimization than that before optimization, and the axle vibration amplitude on a bearing of the rotor is far smaller than the allowable maximum amplitude of dynamic balance. Theoretically, the rotor can directly pass in-plant high-speed dynamic balance without other means such as balance weights through the optimization scheme, and the in-plant high-speed dynamic balance efficiency is improved. According to the method, the in-plant dynamic balance testing ability and efficiency of the rotor can be obviously improved for manufacturing enterprises.

Description

Gas turbine pull rod rotor high-speed balancing ability Optimization Design with end-tooth
Technical field：
The present invention relates to gas turbine technology field, the high quick-action of gas turbine pull rod rotor more particularly to end-tooth is put down Weighing apparatus ability Optimization Design.
Background technology：
Heavy duty gas turbine rod fastening rotor is a kind of typical composite fabricated rotor, by a center pull rod or many circumferences Pull bar passes through wheel discs at different levels, by applying pretightning force the stay-bolt tight two ends spindle nose to pull bar, wheel disc is compressed to incite somebody to action Combined rotor is combined as a whole.As the rotor weight of this structure is light, it is easily assembled and with good cooling effect, in combustion It is widely applied in turbine aircraft turbine engine and aero-engine.In gas turbine wheel disk manufacture process, machining is inaccurate, So that there is amount of unbalance on rotor, at high speed, very big uneven exciting force is produced, causes unit vibration.For end The gas turbine rotor structure of face tooth connection, by adjusting end-tooth setting angle, can improve the effect of rotor high-speed balancing Rate.
The content of the invention：
It is an object of the invention to provide a kind of optimization of the gas turbine pull rod rotor high-speed balancing ability with end-tooth Method for designing, the method provide the relation between wheel disc radial run-out and rotor unbalance value, are that the amount of unbalance of rotor determines Reference is provided.And according to both relations, optimize wheel disc setting angles at different levels, the uneven centrifugal force that amount of unbalance is produced with Unbalanced moments is down to minimum, and then reduces vibratory response amplitude at rotor bearing, reduces the purpose of rotor oscillation.
To reach above-mentioned purpose, the present invention adopts the following technical scheme that to realize：
Gas turbine pull rod rotor high-speed balancing ability Optimization Design with end-tooth, comprises the following steps：
1) the radial run-out degree e according to the front spindle nose of gas turbine pull rod rotor, rear spindle nose and wheel disc at different levels, it is determined that entirely The initial size and PHASE DISTRIBUTION of rotor difference part amount of unbalance；
2) initial size and PHASE DISTRIBUTION according to amount of unbalance, determines uneven centrifugal force to be optimized and each imbalance Centrifugal force to rotor midpoint moment of flexure be object function；
3) according to object function work out genetic algorithm optimization program, using genetic algorithm obtain object function minima and Its corresponding wheel disc end-tooth setting angle；
4) by contrasting initial settling angle degree and optimizing the unbalance response of setting angle lower rotor part, generator terminal of calming the anger after optimization At bearing, axle amplitude first-order kernel peak-fall amplitude is more than 95%, and turbine stub shaft is held under place's axle amplitude first-order kernel peak value Range of decrease degree is more than 95%；After optimization, at compressor end bearing, axle amplitude second-order response peak-fall amplitude is more than 95%, turbine At end bearing, axle amplitude second-order response peak-fall amplitude is more than 80%, determines genetic algorithm to the high quick-action of gas turbine rotor The effectiveness of balance.
The present invention is further improved by, and the gas turbine pull rod rotor carries end face tooth structure, between adjacent wheel disc Connected by end-tooth, end-tooth attachment structure is used to adjust wheel disc setting angle.
The present invention is further improved by, step 1) in, the relation between radial run-out degree e and amount of unbalance is：
Wherein, q is amount of unbalance, and e is radial run-out degree, and m is this grade of wheel disc quality.
The present invention is further improved by, step 2) in, optimization object function is：
The vector of uneven centrifugal force and out-of-balance force moment of flexure is expressed as：
Wherein, q (i) represents the amount of unbalance/gmm of wheel discs at different levels；α (i) expression amount of unbalance phase places/°, it is hereditary calculation Variable in method, i.e., corresponding wheel disc setting angle；K represents wheel disc series；ω is rotor speed/rmin-1；L (i) is represented Distance/mm of the wheel disc amount of unbalances at different levels to rotor midpoint position；I spans are 1～25；FxFor x directions it is uneven from Mental and physical efforts/N；FyFor y directions imbalance centrifugal force/N；F is total imbalance centrifugal force/N；MxFor x directions out-of-balance force moment of flexure/Nm； MyFor y directions out-of-balance force moment of flexure/Nm；M is total out-of-balance force moment of flexure/Nm.
Compared with prior art, the beneficial effects of the present invention is：
The present invention gives the gas turbine pull rod rotor dynamic balancing ability Optimization Design with end face tooth structure, should Method provides one kind side to the optimization of the rotor dynamic balancing ability with end face tooth structure by adjusting wheel disc end-tooth setting angle Method.By the optimization method, before and after optimization, at compressor end bearing, axle amplitude first-order kernel peak-fall amplitude is more than 95%, Turbine stub shaft holds place's axle amplitude first-order kernel peak-fall amplitude and is more than 95%；Before and after optimization, at compressor end bearing, axle shakes Width second-order response peak-fall amplitude is more than 95%, and the turbine stub shaft place of holding axle amplitude second-order response peak-fall amplitude is more than 80%, therefore the method can effectively improve the ability that manufacturer carries out rotor dynamic balancing.The method is applied to the phases such as space flight, electric power Rotor part of the industry with end face tooth structure is closed, with extensive future in engineering applications.
Description of the drawings：
Fig. 1 is certain center pull rod gas turbine rotor typical structure schematic diagram, and rotor end-face Chi He centers are given in figure Tiebar structure.
Fig. 2 is gas turbine wheel disk amount of unbalance schematic diagram.
Fig. 3 is each position circular runout schematic diagram of gas turbine rotor.
Provide 25 circular runout positions in figure altogether, wherein S1, S2, S3 are spindle nose position radius run-out degree in front and back, C21, C2 ... C15 are compressor disk radius run-out degree, and N1, N2, N3 are jackshaft radius run-out degree, and T1, T2, T3, T4 are turbine Wheel disc radius run-out degree.
Fig. 4 is that gas turbine rotor unbalanced moment produces schematic diagram.
Fig. 5 is axle amplitude at compressor end bearing before and after gas turbine pull rod rotor unbalance phase optimization.
Fig. 6 is the turbine stub shaft place of holding axle amplitude before and after gas turbine pull rod rotor unbalance phase optimization.
Fig. 7 is axle amplitude at bearing after gas turbine pull rod rotor unbalance phase optimization.
Fig. 8 is the structural representation of end-tooth.
Specific embodiment：
Below in conjunction with the accompanying drawings the present invention is described in further detail.
Fig. 1 is certain combustion engine center pull rod rotor typical structure schematic diagram, and rotor wheel disc at different levels is by end-tooth torsion pass, employing Center pull rod applies pretightning force.
Referring to Fig. 2 to Fig. 8, gas turbine pull rod rotor dynamic balancing ability optimization design of the present invention with end face tooth structure Method, comprises the following steps：
1) determination of amount of unbalance suffered by gas turbine rotor.
To obtain the data of each part amount of unbalance of whole rotor, according to the gas turbine rotor antero posterior axis that manufacturer provides Head, the radial run-out degree of wheel disc at different levels obtain the eccentric throw and unbalance phase of each part.Wherein eccentric throw δ and radially circle jump The relation of dynamic degree e is；According to eccentric throw and the result of unbalance phase, it is determined that whole rotor initial unbalance, Distribution, each part of whole rotor have the position for needing to add amount of unbalance at 25, the relation between amount of unbalance and eccentric throw For：Q=m δ, and then obtain the relation between amount of unbalance and radius run-out degree and be：Determine that each part of rotor is uneven Weigh, wherein, q is amount of unbalance, and e is radial run-out degree, and m is this grade of wheel disc quality.Fig. 2 gives wheel disc amount of unbalance Schematic diagram, which produces amount of unbalance component in x directions and y directions.Fig. 3 gives the distribution of whole rotor unbalance value, has At 25, amount of unbalance is applied to rotor position.
2) determination of gas turbine rotor imbalance centrifugal force and out-of-balance force moment of flexure optimization object function.
Amount of unbalance component of the amount of unbalance in x directions and y directions can produce the uneven centrifugal force F of respective directionx, Fy With out-of-balance force moment Mx, My, Fig. 4 provides the mechanism of production of out-of-balance force moment of flexure.Uneven centrifugal force and out-of-balance force moment of flexure are made With making rotor produce vibration, according to uneven centrifugal force and out-of-balance force moment of flexure mechanism of production, it is determined that uneven centrifugal force and not The optimization object function of equilibrant moment of flexure is：
The vector of uneven centrifugal force and moment of flexure is represented by：
Wherein, q (i) represents the amount of unbalance/gmm of wheel discs at different levels；α (i) expression amount of unbalance phase places/°, it is hereditary calculation Variable in method；K represents wheel disc series；L (i) represents wheel disc amount of unbalances at different levels to the distance/mm of rotor midpoint position； ω is rotor speed/rmin-1；I spans are 1～25；FxFor x directions imbalance centrifugal force/N；FyIt is uneven for y directions Centrifugal force/N；F is total imbalance centrifugal force/N；MxFor x directions out-of-balance force moment of flexure/Nm；MyFor y directions out-of-balance force moment of flexure/ N·m；M is total out-of-balance force moment of flexure/Nm.
3) determination of the minima and its corresponding wheel disc established angle of uneven centrifugal force and moment of flexure.
According to uneven centrifugal force and out-of-balance force moment of flexure optimization object function, genetic algorithm optimization program, wherein α are worked out I () is the variable in optimized algorithm.By the established angle for adjusting wheel discs at different levels, determine the minima of object function, i.e., it is uneven The minima of weighing apparatus centrifugal force and moment of flexure, the established angle that its corresponding setting angle as needs.Needs are particularly pointed out, for end face The special construction of tooth connection, as the whole circle of wheel disc end-tooth has 180 teeth, therefore the established angle to calculating is rounded and is protected The setting angle difference for demonstrate,proving adjacent wheel disc is even number.
4) contrast the unbalance response of initial settling angle degree and optimization setting angle lower rotor part.
For checking optimization wheel disc setting angle reliability, using rotor unbalance method of response calculation to before and after optimization not Equilibrium response amplitude is contrasted, and after optimization, the unbalance response amplitude of rotor is reduced, and axle amplitude of the rotor at bearing is little The maximum amplitude allowed when dynamic balancing.
After optimization established angle carry out unbalance responses and with optimization before unbalance responses Comparative result.Optimization In front and back at compressor end bearing axle amplitude as shown in figure 5, optimization after first-order kernel peak value drop to 0.802 μm from 482 μm, Fall is more than 95%；60.90 μm from before optimization of second-order response peak value drops to 2.91 μm, and fall is more than 95%.
Optimize forward and backward turbine stub shaft place's axle amplitude is held as shown in fig. 6, single order peak value of response declines from 521 μm after optimization To 0.843 μm, fall is more than 95%；9.48 μm from before optimization of second-order response peak value drops to 1.88 μm.Fall More than 80%.
Calm the anger generator terminal and the turbine stub shaft place of holding axle amplitude after optimization is as shown in fig. 7, after optimization under single order peak value of response The axle amplitude of drop, turbine end and generator terminal of calming the anger is respectively less than 1 μm；Second-order response peak value after optimization declines before relatively optimizing, turbine The axle amplitude of end and generator terminal of calming the anger is respectively less than 3 μm；When working speed is 3000r/min, the axle of turbine end and generator terminal of calming the anger shakes Amplitude is respectively less than 2.3 μm.
Before and after the optimization of 1 gas turbine rotor of table, unbalance response axle shakes the analysis of single magnitude determinations Comparative result

Claims (4)

1. the gas turbine pull rod rotor high-speed balancing ability Optimization Design with end-tooth, it is characterised in that include with Lower step：
1) the radial run-out degree e according to the front spindle nose of gas turbine pull rod rotor, rear spindle nose and wheel disc at different levels, it is determined that whole rotor The initial size and PHASE DISTRIBUTION of different part amount of unbalances；
2) initial size and PHASE DISTRIBUTION according to amount of unbalance, determines uneven centrifugal force to be optimized and each uneven centrifugation Power to rotor midpoint moment of flexure be object function；
3) genetic algorithm optimization program is worked out according to object function, the minima of object function and its right is obtained using genetic algorithm The wheel disc end-tooth setting angle answered；
4) by contrasting initial settling angle degree and optimizing the unbalance response of setting angle lower rotor part, compressor end bearing after optimization Place's axle amplitude first-order kernel peak-fall amplitude is more than 95%, and turbine stub shaft holds place's axle amplitude first-order kernel peak-fall width Degree is more than 95%；After optimization, at compressor end bearing, axle amplitude second-order response peak-fall amplitude is more than 95%, turbine stub shaft Place's axle amplitude second-order response peak-fall amplitude is held more than 80%, determines genetic algorithm to gas turbine rotor high-speed balancing Effectiveness.
2. the gas turbine pull rod rotor high-speed balancing ability optimization design side with end-tooth according to claim 1 Method, it is characterised in that the gas turbine pull rod rotor carries end face tooth structure, is connected by end-tooth between adjacent wheel disc, end Face tooth attachment structure is used to adjust wheel disc setting angle.
3. the gas turbine pull rod rotor high-speed balancing ability optimization design side with end-tooth according to claim 1 Method, it is characterised in that step 1) in, the relation between radial run-out degree e and amount of unbalance is：
q = e · m 2
Wherein, q is amount of unbalance, and e is radial run-out degree, and m is this grade of wheel disc quality.
4. the gas turbine pull rod rotor high-speed balancing ability optimization design side with end-tooth according to claim 1 Method, it is characterised in that step 2) in, optimization object function is：
F x = Σ i = 1 k q ( i ) × c o s ( α ( i ) ) × ω 2 F y = Σ i = 1 k q ( i ) × sin ( α ( i ) ) × ω 2 M x = Σ i = 1 k L ( i ) × q ( i ) × sin ( α ( i ) ) × ω 2 M y = Σ i = 1 k L ( i ) × q ( i ) × cos ( α ( i ) ) × ω 2
The vector of uneven centrifugal force and out-of-balance force moment of flexure is expressed as：
F = F x 2 + F y 2 M = M x 2 + M y 2
Wherein, q (i) represents the amount of unbalance/gmm of wheel discs at different levels；α (i) expression amount of unbalance phase places/°, in being genetic algorithm Variable, i.e., corresponding wheel disc setting angle；K represents wheel disc series；ω is rotor speed/rmin-1；L (i) represents at different levels Distance/mm of the wheel disc amount of unbalance to rotor midpoint position；I spans are 1～25；FxFor x directions imbalance centrifugal force/ N；FyFor y directions imbalance centrifugal force/N；F is total imbalance centrifugal force/N；MxFor x directions out-of-balance force moment of flexure/Nm；MyFor y Direction out-of-balance force moment of flexure/Nm；M is total out-of-balance force moment of flexure/Nm.
CN201610069281.5A 2016-02-01 2016-02-01 High-speed dynamic balance ability optimization design method for gas turbine pull rod rotor with end face teeth Expired - Fee Related CN105736059B (en)

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CN106121733B (en) * 2016-08-12 2019-01-11 上海电气燃气轮机有限公司 A kind of mixed rotor structure and assemble method for heavy duty gas turbine
CN106372365A (en) * 2016-09-29 2017-02-01 西安交通大学 Shafting centering calculation method of novel shafting structure under specific centering requirement
CN108225783B (en) * 2016-12-15 2020-01-31 中国航发商用航空发动机有限责任公司 Method and device for balancing fan rotor of aviation turbofan engine
CN107895077B (en) * 2017-11-10 2020-03-17 西安交通大学 Gas turbine pull rod rotor assembly parameter optimization method considering multiple disk and drum manufacturing factors
CN109740260B (en) * 2019-01-04 2023-07-21 岭澳核电有限公司 Dynamic balance processing method and device for steam turbine rotor
CN112097995B (en) * 2020-09-17 2022-08-12 中国航发成都发动机有限公司 Balance adjusting device and method for turbofan engine rotor single-stage disc
CN113107676B (en) * 2021-05-19 2022-05-27 中国科学院工程热物理研究所 Three-layer sleeve type central pull rod device

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CN101639395A (en) * 2009-08-31 2010-02-03 西安交通大学 Improved holographic dynamic balancing method of high-speed main shaft
US8015127B2 (en) * 2006-09-12 2011-09-06 New York University System, method, and computer-accessible medium for providing a multi-objective evolutionary optimization of agent-based models
CN103970944A (en) * 2014-04-29 2014-08-06 西安交通大学 Design and check method for pre-tightening force of rod fastening rotor of gas turbine with wheel disks in plane contact
CN104018887A (en) * 2014-05-29 2014-09-03 西安交通大学 Pulling rod rotor pre-tightening force designing verification method of combustion gas turbine with end face teeth between wheel discs in contact

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CN101639395A (en) * 2009-08-31 2010-02-03 西安交通大学 Improved holographic dynamic balancing method of high-speed main shaft
CN103970944A (en) * 2014-04-29 2014-08-06 西安交通大学 Design and check method for pre-tightening force of rod fastening rotor of gas turbine with wheel disks in plane contact
CN104018887A (en) * 2014-05-29 2014-09-03 西安交通大学 Pulling rod rotor pre-tightening force designing verification method of combustion gas turbine with end face teeth between wheel discs in contact

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