CN109583063A - A kind of kinetic characteristics similar Design method of fan propeller test model - Google Patents
A kind of kinetic characteristics similar Design method of fan propeller test model Download PDFInfo
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Abstract
A kind of fan propeller experimental model kinetic characteristics similar Design method, initially sets up the finite element model of low pressure rotor tester, calculates its characteristics of mode.Then fan propeller experimental model is established, determines that fan propeller or so point supporting rigidity in experimental model, Low Pressure Turbine Rotor simplify wheel disc quality in section shaft internal-and external diameter and shaft, diameter rotary inertia to the affecting laws of this model characteristics of mode.Finally according to above-mentioned gained rule, adjusting each parameter keeps the kinetic characteristics of fan propeller in fan propeller experimental model consistent with the kinetic characteristics of fan propeller in low pressure rotor system.The present invention is when designing fan propeller tester, consider coupling of the Low Pressure Turbine Rotor to fan propeller, Low Pressure Turbine Rotor is simplified, the general conclusion for adjusting Modal Method in fan propeller experimental model design process is obtained by above-mentioned similar Design.Convenient for the research to aerial engine fan rotor-support-foundation system genuine property.
Description
Technical field
The present invention relates to aircraft engine rotor system technical field more particularly to a kind of fan propeller test model power
Learn characteristic similar Design method.
Background technique
Low pressure rotor system is the key component of fanjet, by fan propeller and Low Pressure Turbine Rotor two parts group
At.The dependent dynamics specificity analysis carried out at present about fan propeller is provided to rotor-support-foundation system in reflection actual engine
Dependent dynamics characteristic.It is all by wind however when currently carrying out corresponding calculating research or experimental study to fan propeller system
Fan rotor, which is directly pulled out from low pressure rotor system, to be come.The connection between fan propeller and Low Pressure Turbine Rotor is not accounted for wind
Fan the influence of rotor.In fact, there are couplings between Low Pressure Turbine Rotor and fan propeller due to the presence of connection.It will
Fan section in low pressure rotor system intercepts out, constant in structure type and bearing position, and does not consider Low Pressure Turbine Rotor
When with its coupled relation, only by adusting the size of fan propeller support stiffness, it is difficult to make the dynamic of independent fan propeller system
Mechanical characteristic is consistent with the kinetic characteristics of fan propeller in low pressure rotor system.
Fan propeller under reaction real conditions can not be illustrated how about the relevant calculation of fan propeller system in the past
Correlation properties.Therefore for independent fan propeller system, make the kinetic characteristics of its reaction and be in low pressure rotor system
The kinetic characteristics of middle fan propeller unanimously require study.Since actual engine rotor itself is sufficiently complex, it is not easy to analyze,
Therefore the present invention is analyzed using Rotor test device.
Summary of the invention
In order to overcome the shortcomings in the prior art, it is similar to provide a kind of fan propeller test model kinetic characteristics by the present invention
Design method initially sets up low pressure rotor exerciser finite element model, calculates its characteristics of mode.Then fan propeller test is established
Model determines relevant parameter to the affecting laws of this model characteristics of mode.Finally according to above-mentioned gained rule, adjusting each parameter makes
The kinetic characteristics of fan propeller are consistent with the kinetic characteristics of fan propeller in low pressure rotor system in this test model.
The specific technical proposal of the invention is:
A kind of fan propeller test model kinetic characteristics similar Design method, includes the following steps:
Step 1: establish low pressure rotor exerciser finite element model and calculate its characteristics of mode, using FInite Element to containing
When covering the low pressure rotor system modelling of gear coupling, the nodes for gear coupling will be covered being considered as two coincidences, transverse direction at node and
Rotation stiffness is respectively the transverse direction and rotation stiffness for covering gear coupling；If the i-th node of fan propeller and Low Pressure Turbine Rotor
Jth node is coupled with set gear coupling, and the radial rigidity of shaft coupling is Kr, angular stiffness KtIf the i-th node of fan propeller
Displacement are as follows: xi、yi、θix、θiy, the displacement of j-th of node of Low Pressure Turbine Rotor is xj、yj、θjx、θjy.Then act on fan propeller
Power and torque F in node iix、Fiy、Mix、MiyAre as follows:
The power and torque that act on Low Pressure Turbine Rotor node j and act on the power and torque in fan propeller node i
It is equal in magnitude contrary.
The Coupling stiffness matrix K of this low pressure rotor systemcAre as follows:
The undamped-free vibration differential equation of this low pressure rotor system are as follows:
In formula,K1, M1For fan propeller system stiffness matrix and
Mass matrix；K2, M2For the stiffness matrix and mass matrix of Low Pressure Turbine Rotor system；X is the generalized displacement vector of system；
For the generalized acceleration vector of system.
Solving equation (4) to rotor-support-foundation system can be obtained the characteristics of mode of low pressure rotor system.
Step 2: establishing fan propeller test model, fan propeller system right end is coupled one section by set gear coupling
Axis and a wheel disc are to simulate effect of the Low Pressure Turbine Rotor to fan propeller.
Step 3: determining that fan propeller or so point supporting rigidity advises its Effect of Mode in fan propeller test model
Rule.
Setting influences the other parameters value of fan propeller test model characteristics of mode, and the bearing of fixed one of fulcrum is rigid
Degree, allows the support stiffness of another fulcrum to change, and calculates variation of the fan propeller mode with it.
Step 4: determining that the connected Low Pressure Turbine Rotor of fan propeller right end simplifies shaft part internal-and external diameter and advises to its Effect of Mode
Rule.
Setting influences the other parameters value of fan propeller test model characteristics of mode, and fixed one of diameter of axle size permits
Perhaps another diameter of axle changes, and calculates variation of the fan propeller mode with it.
Step 5: determining that the connected Low Pressure Turbine Rotor of fan propeller right end simplifies wheel disc quality on shaft part, diameter rotation is used to
Amount is to its Effect of Mode rule.
Setting influences the other parameters value of fan propeller test model characteristics of mode, and fixed wheel disc quality, diameter rotation are used
A parameter in amount allows another Parameters variation, calculates variation of the fan propeller mode with it.
Step 6: coordinating to adjust each parameter, selecting makes wind according to above-mentioned each parameter to the affecting laws of fan propeller mode
Fan fan propeller parameters similar with fan rotor dynamic behavior in low pressure rotor system in rotor test model.
Beneficial effects of the present invention:
The present invention turns low-pressure turbine by considering the coupling between fan propeller system and Low Pressure Turbine Rotor system
Son carries out corresponding simplify and handles, and is included in influence of the Low Pressure Turbine Rotor system to fan propeller system.Quantitative analysis fan propeller
Fan propeller or so point supporting rigidity, Low Pressure Turbine Rotor simplify section shaft internal-and external diameter, wheel disc quality, diameter in test model
Rotary inertia obtains in fan propeller test model design process to the capability of influence of two rank mode before fan propeller and adjusts mould
The general conclusion of state method.Convenient for the research to aerial engine fan rotor-support-foundation system genuine property.
Detailed description of the invention
Fig. 1 is low pressure rotor exerciser finite element model of the present invention；
Fig. 2 is fan propeller test model of the present invention；
Fig. 3 for Fig. 1 institute of the present invention representation model apoplexy fan rotor one, second_mode；
Fig. 4 is Fig. 2 institute of the present invention representation model intrinsic frequency with the variation of the right point supporting rigidity of fan propeller；
Fig. 5 fans rotor vibration model with the variation of its right point supporting rigidity for Fig. 2 institute of the present invention representation model apoplexy；
Fig. 6 is Fig. 2 institute of the present invention representation model intrinsic frequency with the variation of the left point supporting rigidity of fan propeller；
Fig. 7 fans rotor vibration model with the variation of its left point supporting rigidity for Fig. 2 institute of the present invention representation model apoplexy；
Fig. 8 is Fig. 2 institute of the present invention representation model intrinsic frequency with the variation of fan propeller institute connecting shaft section outer diameter；
Fig. 9 fans rotor vibration model with the variation of its connecting shaft section outer diameter for Fig. 2 institute of the present invention representation model apoplexy；
Figure 10 is Fig. 2 institute of the present invention representation model intrinsic frequency with the variation of fan propeller institute connecting shaft section internal diameter；
Figure 11 fans rotor vibration model with the variation of its connecting shaft section internal diameter for Fig. 2 institute of the present invention representation model apoplexy；
Figure 12 is Fig. 2 institute of the present invention representation model intrinsic frequency with the variation of wheel disc quality in fan propeller institute connecting shaft section；
Figure 13 fans rotor vibration model with the variation of wheel disc quality in its connecting shaft section for Fig. 2 institute of the present invention representation model apoplexy；
Figure 14 is Fig. 2 institute of the present invention representation model intrinsic frequency with wheel diameter rotary inertia in fan propeller institute connecting shaft section
Variation；
Figure 15 fans rotor vibration model with wheel diameter rotary inertia in its connecting shaft section for Fig. 2 institute of the present invention representation model apoplexy
Variation；
Figure 16 for calculated after adjusting parameter of the present invention Fig. 2 institute representation model apoplexy fan rotor one, second_mode.
Number in Fig. 1, Fig. 2 is the node ID of rotor-support-foundation system finite element model.Fig. 1 interior joint 3,4,10,11 is low
Pressure compressor and 4 turntables being reduced to of low-pressure turbine disk, node 2,5,12 are three fulcrums of low pressure rotor system, node 5,
It is set tooth connection between 6.Fig. 2 interior joint 3,4 is 2 turntables that low-pressure compressor is reduced to, and node 2,5 is the two of fan propeller
A fulcrum, node 6 to node 7 are that Low Pressure Turbine Rotor simplifies part.Set tooth connection is similarly between its interior joint 5,6.
Fig. 3, Fig. 5, Fig. 7, Fig. 9, Figure 11, Figure 13, Figure 15, Tu16Zhong: (a) -1 first order mode；(b) -2 first order mode.
Specific embodiment
In order to make the present invention technical method, target and the effect realized be readily apparent from understanding, below with reference to an example into one
Step illustrates the present invention.
A kind of fan propeller test model kinetic characteristics similar Design method, it is limited to initially set up low pressure rotor exerciser
Meta-model, as shown in Figure 1, calculating its characteristics of mode.Then fan propeller test model is established, as shown in Figure 2.Determine corresponding ginseng
Several affecting laws to this model characteristics of mode.Finally according to above-mentioned gained rule, adjusting each parameter makes this test model apoplexy
The kinetic characteristics for fanning rotor are consistent with the kinetic characteristics of fan propeller in low pressure rotor system.Specific step is as follows:
Step 1: establishing low pressure rotor exerciser finite element model as shown in Figure 1, calculating its characteristics of mode.Using limited
When first method is to the low pressure rotor system modelling of the gear coupling containing set, the nodes that gear coupling is considered as two coincidences will be covered, at node
Transverse direction and rotation stiffness be respectively cover gear coupling transverse direction and rotation stiffness.If Section 5 point of fan propeller and low pressure whirlpool
Section 6 point for taking turns rotor is coupled with set gear coupling, and the radial rigidity of shaft coupling is 1.35 × 108N/m, angular stiffness 1.95
×106Nm/rads (does not consider damping effect), if the displacement of fan propeller Section 5 point are as follows: x5、y5、θ5x、θ5y, low-pressure turbine
The displacement of the 6th node of rotor is x6、y6、θ6x、θ6y.Then act on the power and torque F on fan propeller node 55x、F5y、M5x、
M5yAre as follows:
The power and torque that act on Low Pressure Turbine Rotor node 6 and act on the power and torque on fan propeller node 5
It is equal in magnitude contrary.
The Coupling stiffness matrix K of this low pressure rotor systemcAre as follows:
The undamped-free vibration differential equation of this low pressure rotor system are as follows:
In formula,K1, M1For fan propeller system stiffness matrix and
Mass matrix；K2, M2For the stiffness matrix and mass matrix of Low Pressure Turbine Rotor system；X is the generalized displacement vector of system；
For the generalized acceleration vector of system.
Solving equation (4) to rotor-support-foundation system can be obtained the characteristics of mode of low pressure rotor system, calculate to obtain low pressure shown in Fig. 1
The preceding two ranks intrinsic frequency of fan propeller is 62.0Hz, 116.6Hz in rotor-support-foundation system, and the corresponding vibration shape is as shown in Figure 3.
Step 2: establishing fan propeller test model, as shown in Figure 2.Fan propeller system right end is passed through into set tooth shaft coupling
Device is coupled a bit of axis and a wheel disc to the effect of simulating Low Pressure Turbine Rotor to fan propeller.
Step 3: determining that fan propeller or so point supporting rigidity advises its Effect of Mode in fan propeller test model
Rule.
Set first Fig. 2 institute representation model apoplexy fan rotor institute connecting shaft section internal diameter as 0mm, outer diameter 14mm, fan propeller institute
Wheel disc quality is 1.5kg in connecting shaft section, and wheel diameter rotary inertia is 0.00506kg.m2.The left point supporting of fan attachment rotor
Rigidity is 1.15 × 106N/m, calculating Fig. 2 institute representation model is respectively 1 × 10 in the right point supporting rigidity of fan propeller5N/m、5×
105N/m、1×106N/m、5×106N/m、1×107N/m、5×107Preceding two ranks intrinsic frequency such as Fig. 4 institute under six groups of schemes of N/m
Show, the vibration shape of the corresponding Fig. 2 institute representation model apoplexy fan rotor of 6 groups of schemes is as shown in Figure 5.By Fig. 4 it is found that when fan propeller is right
Point supporting is just 1 × 105N/m~1 × 106When N/m rigidity section changes, Fig. 2 institute representation model first natural frequency increases bright
It is aobvious.When the right point supporting of fan propeller is just 1 × 106N/m~1 × 107When N/m rigidity section changes, Fig. 2 institute representation model second order
Intrinsic frequency increases obvious.As shown in Figure 5 when right point supporting rigidity is 5 × 106N/m~1 × 107The variation of N/m rigidity section
When, it is consistent with Fig. 3 institute representation model apoplexy fan rotor vibration model that Fig. 2 institute representation model apoplexy fans the one of rotor, second_mode.
The right point supporting rigidity of fan attachment rotor is 5.43 × 106N/m calculates Fig. 2 institute representation model and turns respectively in fan
The left point supporting rigidity of son is 1 × 105N/m、5×105N/m、1×106N/m、5×106N/m、1×107N/m、5×107N/m six
Preceding two ranks intrinsic frequency under group scheme is as shown in fig. 6, the corresponding Fig. 2 institute representation model apoplexy of 6 groups of schemes fans the vibration shape of rotor such as
Shown in Fig. 7.The left point supporting rigidity of fan propeller is affected to Fig. 2 institute representation model second order intrinsic frequency as shown in Figure 6, to one
Rank intrinsic frequency influences smaller.As shown in Figure 7 when the left point supporting rigidity of fan propeller is 1 × 106When N/m, Fig. 2 institute representation model
One second_mode of middle fan propeller is consistent with fan rotor vibration model in Fig. 3, cross greater than this rigidity when its support stiffness or
It crosses and is less than this rigidity, it is not consistent with Fig. 3 institute representation model apoplexy fan rotor vibration model that Fig. 2 institute representation model apoplexy fans rotor vibration model.
Step 4: determining that the connected Low Pressure Turbine Rotor of fan propeller right end simplifies shaft part internal-and external diameter and advises to its Effect of Mode
Rule.
Setting Fig. 2 institute representation model apoplexy fan rotor or so point supporting rigidity and Fig. 1 institute representation model apoplexy fan rotor first
Left and right point supporting rigidity is consistent, and wheel disc quality value is 1.5kg in fan propeller institute connecting shaft section, and wheel diameter rotary inertia is
0.00506kg·m2.Fan attachment rotor institute connecting shaft section internal diameter is 0mm, calculates fan propeller respectively in its connecting shaft section outer diameter
It is two rank intrinsic frequencies before under five groups of schemes of 10mm, 14mm, 20mm, 30mm, 35mm as shown in figure 8, the corresponding vibration of 5 groups of schemes
Type is as shown in Figure 9.As seen from Figure 8 in limited adjusting range, when institute's connecting shaft section outer diameter is less than 20mm, increase with its value
Two rank intrinsic frequencies increase before fan propeller.And the variation of its value is to two rank intrinsic frequency before fan propeller when its value is more than 20mm
It influences little.When institute, connecting shaft section internal diameter is fixed as shown in Figure 9, as the one of the increase fan propeller of outer diameter, second_mode is basic
It is constant.
Fan attachment rotor institute connecting shaft section outer diameter be 14mm, calculate fan propeller respectively its connecting shaft section internal diameter be 0mm,
Preceding two ranks intrinsic frequency under five groups of schemes of 5mm, 8mm, 10mm, 12mm is as shown in Figure 10, the corresponding vibration shape such as Figure 11 of 5 groups of schemes
It is shown.As seen from Figure 10 in limited adjusting range, the variation of fan propeller institute connecting shaft section internal diameter is to the intrinsic frequency of one, second order
Rate influences less, when internal diameter is greater than 10mm, shows slightly obvious to two rank intrinsic frequencies influence before fan propeller, with internal diameter
Two rank intrinsic frequencies reduce before size increases fan propeller.When fan propeller institute, connecting shaft section outer diameter is fixed as shown in Figure 11, with
The increase fan propeller of internal diameter one, second_mode is basically unchanged.
Step 5: determining that the connected Low Pressure Turbine Rotor of fan propeller right end simplifies wheel disc quality on shaft part, diameter rotation is used to
Amount is to its Effect of Mode rule.
Setting Fig. 2 institute representation model apoplexy fan rotor or so point supporting rigidity and Fig. 1 institute representation model apoplexy fan rotor first
Left and right point supporting rigidity is consistent, and fan propeller institute connecting shaft section internal diameter value is 0mm, and outer diameter value is 14mm.Fan attachment turns
Wheel diameter rotary inertia is 0.0056kgm in sub- institute's connecting shaft section2, calculate fan propeller respectively wheel disc quality be 1kg,
Preceding two ranks intrinsic frequency under five groups of schemes of 1.5kg, 10kg, 20kg, 30kg is as shown in figure 12, and the corresponding vibration shape of 5 groups of schemes is such as
Shown in Figure 13.As seen from Figure 12 in limited adjusting range, when one timing of wheel diameter rotary inertia, wheel disc quality is got over
Greatly, fan propeller first natural frequency is lower, and second order intrinsic frequency varies less.As shown in Figure 13 when wheel diameter rotation is used
Amount is fixed, as the one of the increase fan propeller of wheel disc quality, second_mode are basically unchanged.
Wheel disc quality is 1.5kg in fan attachment rotor institute connecting shaft section, calculates fan propeller and rotates respectively in wheel diameter
Inertia is 0.001kgm2、0.00506kg·m2、0.01kg·m2、0.02kg·m2、0.03kg·m2Before under five groups of schemes
Two rank intrinsic frequencies are as shown in figure 14, and the corresponding vibration shape of 5 groups of schemes is as shown in figure 15.As seen from Figure 14 in limited adjustment model
In enclosing, when one timing of wheel disc quality, wheel diameter rotary inertia is bigger, and fan propeller first natural frequency is lower, and second order is solid
There is frequency to vary less.As shown in Figure 15 when wheel disc quality is fixed, with the increase fan propeller of wheel diameter rotary inertia
One, second_mode is basically unchanged.
Step 6: coordinating to adjust each parameter, selecting makes wind according to above-mentioned each parameter to the affecting laws of fan propeller mode
Fan fan propeller parameters similar with fan rotor dynamics in low pressure rotor system in rotor test model.
There was only Fig. 2 institute representation model apoplexy fan rotor or so branch in this example in certain adjusting range, in above-mentioned each parameter
Dot point rigidity has an impact to fan propeller one, second_mode, influence pole of the other parameters to fan propeller one, second_mode
It is small, select one group of support stiffness to make the one of Fig. 2 institute representation model apoplexy fan rotor, second_mode and Fig. 1 institute representation model by above-mentioned rule
Middle fan propeller one, second_mode are consistent.The left point supporting rigidity of primary election is 1.15 × 10 in the present invention6N/m, right point supporting
Rigidity is 5.43 × 106N/m.When the vibration shape is similar, simplify shaft part by adjusting the connected Low Pressure Turbine Rotor of fan propeller right end
Internal-and external diameter, wheel disc quality, diameter rotary inertia obtain and the consistent intrinsic frequency of Fig. 1 institute representation model.
If Fig. 2 institute representation model apoplexy, which fans rotor first natural frequency, is higher than Fig. 1 institute representation model, fan propeller can be increased
Institute's connecting shaft section internal diameter, wheel disc quality or diameter rotary inertia, three kinds of schemes can also carry out simultaneously.When first natural frequency is lower than figure
When 1 representation model, adjust in the opposite direction.Second order intrinsic frequency is only more sensitive to support stiffness variation, and fan turns
The left point supporting rigidity of son is affected to Fig. 2 institute representation model second order intrinsic frequency, influences on first natural frequency smaller.Therefore
After regulating first natural frequency, it can guarantee the constant rigidity section adjustment left point supporting rigidity of fan propeller of the vibration shape
Size, other parameters can make Fig. 2 institute representation model apoplexy fan rotor and Fig. 1 institute representation model apoplexy fan rotor one, two under fine tuning
Rank intrinsic frequency is consistent.
Adjusting parameters according to above-mentioned general conclusion can proper Fig. 2 institute according to the inherent characteristic of Fig. 1 institute representation model
The left point supporting rigidity of fan propeller is 1 × 10 in representation model6N/m, right point supporting rigidity are 5.43 × 106N/m, fan turn
The sub- simplified shaft part outer diameter of the connected Low Pressure Turbine Rotor of right end is 14mm, internal diameter 0mm, wheel disc quality are 1.2kg, wheel diameter turns
Dynamic inertia is 0.008kgm2When obtain optimal design, Fig. 2 institute representation model first natural frequency is 61.3Hz at this time, and second order is solid
Having frequency is 116.8Hz, and the vibration shape is as shown in figure 16.The program and the characteristics of mode of Fig. 1 institute representation model are almost the same, meet design
It is required that.
So far, the kinetic characteristics similar Design process of fan propeller test model terminates, and passes through this example optimal wind
The relevant parameter for fanning rotor test model, meets proposed demanding kinetics.
Claims (4)
1. a kind of fan propeller test model kinetic characteristics similar Design method, which is characterized in that comprise the following steps that
Step 1: establishing low pressure rotor exerciser finite element model and calculating its characteristics of mode, using FInite Element to the tooth containing set
When the low pressure rotor system modelling of shaft coupling, gear coupling will be covered and be considered as two nodes being overlapped, transverse direction and corner at node
Rigidity is respectively to cover the transverse direction and rotation stiffness of gear coupling；If the i-th node of fan propeller and the jth section of Low Pressure Turbine Rotor
Point is coupled with set gear coupling, and the radial rigidity of shaft coupling is Kr, angular stiffness KtIf the displacement of the i-th node of fan propeller
Are as follows: xi、yi、θix、θiy, the displacement of j-th of node of Low Pressure Turbine Rotor is xj、yj、θjx、θjy；Then act on fan propeller node i
On power and torque Fix、Fiy、Mix、MiyAre as follows:
The power and torque that act on Low Pressure Turbine Rotor node j and act on the power and torque size in fan propeller node i
Equal direction is opposite；
The Coupling stiffness matrix K of this low pressure rotor systemcAre as follows:
The undamped-free vibration differential equation of this low pressure rotor system are as follows:
In formula,K1, M1For the stiffness matrix and quality of fan propeller system
Matrix；K2, M2For the stiffness matrix and mass matrix of Low Pressure Turbine Rotor system；X is the generalized displacement vector of system；To be
The generalized acceleration vector of system；
Solving equation (4) to rotor-support-foundation system can be obtained the characteristics of mode of low pressure rotor system；
Step 2: establish fan propeller test model, by fan propeller system right end by set gear coupling be coupled one section of axis with
One wheel disc is to simulate effect of the Low Pressure Turbine Rotor to fan propeller；
Step 3: determining that fan propeller or so point supporting rigidity is to its Effect of Mode rule in fan propeller test model；
Step 4: determining that the connected Low Pressure Turbine Rotor of fan propeller right end simplifies shaft part internal-and external diameter to its Effect of Mode rule；
Step 5: determining that the connected Low Pressure Turbine Rotor of fan propeller right end simplifies wheel disc quality, diameter rotary inertia pair on shaft part
Its Effect of Mode rule；
Step 6: coordinating to adjust each parameter, selecting turns fan according to above-mentioned each parameter to the affecting laws of fan propeller mode
Fan propeller parameters similar with fan rotor dynamic behavior in low pressure rotor system in sub- test model.
2. a kind of fan propeller test model kinetic characteristics similar Design method according to claim 1, feature exist
In step 3: setting influences the other parameters value of fan propeller test model characteristics of mode, the bearing of fixed one of fulcrum
Rigidity allows the support stiffness of another fulcrum to change, and calculates variation of the fan propeller mode with it.
3. a kind of fan propeller test model kinetic characteristics similar Design method according to claim 1, feature exist
In, step 4: setting influences the other parameters value of fan propeller test model characteristics of mode, one of diameter of axle size is fixed,
Allow another diameter of axle to change, calculates variation of the fan propeller mode with it.
4. a kind of fan propeller test model kinetic characteristics similar Design method according to claim 1, feature exist
In step 5: setting influences the other parameters value of fan propeller test model characteristics of mode, fixed wheel disc quality, diameter rotation
A parameter in inertia allows another Parameters variation, calculates variation of the fan propeller mode with it.
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050278127A1 (en) * | 2003-05-29 | 2005-12-15 | Griffin Jerry H | Determination of damping in bladed disk systems using the fundamental mistuning model |
| KR20090034112A (en) * | 2007-10-02 | 2009-04-07 | 주식회사 삼진금속 | Manufacturing method of coupling bolt for gas turbine |
| CN102201033A (en) * | 2011-04-21 | 2011-09-28 | 西北工业大学 | Method for analyzing dynamics of aviation multi-rotor coupling system |
| GB201506197D0 (en) * | 2015-04-13 | 2015-05-27 | Rolls Royce Plc | Rotor damper |
| CN204705483U (en) * | 2015-06-05 | 2015-10-14 | 湖南科技大学 | A kind of aeromotor birotor Research on Dynamic Characteristic experiment porch |
| CN105278349A (en) * | 2015-11-23 | 2016-01-27 | 哈尔滨工业大学 | Aero-engine simulation test bed on the basis of birotor simplified dynamic model design |
| CN105740507A (en) * | 2016-01-22 | 2016-07-06 | 中国航空动力机械研究所 | Equivalent modeling method for complex rotor system of aero-engine |
| CN106503375A (en) * | 2016-10-28 | 2017-03-15 | 山东大学 | One kind is based on CNThe theoretical method and system for determining turbine rotor critical speed of group |
| CN108350744A (en) * | 2015-10-28 | 2018-07-31 | 赛峰飞机发动机公司 | Method for intentionally making the turbine flabellum of turbine lack of proper care |
| CN108663948A (en) * | 2018-05-17 | 2018-10-16 | 西北工业大学 | A kind of design method of aeroengine control system Numerical Simulation Analysis platform |
-
2018
- 2018-11-20 CN CN201811384430.2A patent/CN109583063B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050278127A1 (en) * | 2003-05-29 | 2005-12-15 | Griffin Jerry H | Determination of damping in bladed disk systems using the fundamental mistuning model |
| KR20090034112A (en) * | 2007-10-02 | 2009-04-07 | 주식회사 삼진금속 | Manufacturing method of coupling bolt for gas turbine |
| CN102201033A (en) * | 2011-04-21 | 2011-09-28 | 西北工业大学 | Method for analyzing dynamics of aviation multi-rotor coupling system |
| GB201506197D0 (en) * | 2015-04-13 | 2015-05-27 | Rolls Royce Plc | Rotor damper |
| CN204705483U (en) * | 2015-06-05 | 2015-10-14 | 湖南科技大学 | A kind of aeromotor birotor Research on Dynamic Characteristic experiment porch |
| CN108350744A (en) * | 2015-10-28 | 2018-07-31 | 赛峰飞机发动机公司 | Method for intentionally making the turbine flabellum of turbine lack of proper care |
| CN105278349A (en) * | 2015-11-23 | 2016-01-27 | 哈尔滨工业大学 | Aero-engine simulation test bed on the basis of birotor simplified dynamic model design |
| CN105740507A (en) * | 2016-01-22 | 2016-07-06 | 中国航空动力机械研究所 | Equivalent modeling method for complex rotor system of aero-engine |
| CN106503375A (en) * | 2016-10-28 | 2017-03-15 | 山东大学 | One kind is based on CNThe theoretical method and system for determining turbine rotor critical speed of group |
| CN108663948A (en) * | 2018-05-17 | 2018-10-16 | 西北工业大学 | A kind of design method of aeroengine control system Numerical Simulation Analysis platform |
Non-Patent Citations (6)
| Title |
|---|
| 王晓峰等: "航空发动机风扇转子试验器动力学特性研究", 《动力学与控制学报》 * |
| 范叶森等: "挠性联轴器耦合多转子系统振动分析的总体耦合矩阵法", 《机械科学与技术》 * |
| 范叶森等: "某涡扇发动机转子系统稳定裕度及其灵敏度分析", 《燕山大学学报》 * |
| 路振勇 等: ""六点支承航空发动机双转子系统动力学离散模型"", 《中国科学：技术科学》 * |
| 陈萌;马艳红;刘书国;洪杰;: "航空发动机整机有限元模型转子动力学分析" * |
| 颜文忠;廖鑫;曹冲;洪杰;: "齿轮传动涡扇发动机低压转子结构与动力学分析" * |
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