CN103970944A - Design and check method for pre-tightening force of rod fastening rotor of gas turbine with wheel disks in plane contact - Google Patents
Design and check method for pre-tightening force of rod fastening rotor of gas turbine with wheel disks in plane contact Download PDFInfo
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Abstract
The invention provides a design and check method for pre-tightening force of a rod fastening rotor of a gas turbine with wheel disks in plane contact. The method includes the first step of calculating the maximum gravity bending moment Mb borne by the rotor of the gas turbine and the position of the maximum gravity bending moment Mb, and determining the torque Mt transmitted in the operating process of the gas turbine, the second step of obtaining the axial moment of inertia Id of cross section to diameter, the polar moment of inertia Ip and the cross-sectional area A, the third step of calculating the maximum disengagement stress sigma generated by gravity at a contact interface where the rotor bears the maximum gravity bending moment and the pressure stress Pa generated by the pre-tightening force F of a pull rod, defining a bending non-dimensional coefficient to be gamma b which meets the equation gamma b=sigma/Pa, setting the pre-tightening force of the pull rod and enabling the bending non-dimensional coefficient to be smaller than 1.0, and the fourth step of calculating the maximum shearing stress theta t generated by torque on the contact interface where the rotor bears the maximum gravity bending moment and the shearing stress theta f generated by maximum static friction force under the effect of the pre-tightening force F, defining a torsion non-dimensional coefficient to be gamma t which meets the equation gamma t=theta t/theta f, and checking the value of the torsion non-dimensional coefficient, wherein when the bending non-dimensional coefficient and the torsion non-dimensional coefficient are both smaller than 1.0, the pre-tightening force of the rod fastening rotor of the gas turbine can ensure that the contact surfaces between the wheel disks do not disengage from each other.
Description
[technical field]
The present invention relates to gas turbine design field, particularly the gas turbine pull rod rotor Prestress design check method of plane contact between a kind of wheel disc.
[background technology]
Heavy duty gas turbine rod fastening rotor is a kind of typical composite fabricated rotor, pass wheel discs at different levels by a center pull rod or many circumferential pull bars, by pull bar being applied to pretightning force and the stay-bolt of tight two ends spindle nose, wheel disc being compressed so that combined rotor is combined as a whole.Because the rotor weight of this structure is light, be easy to assembling and there is good cooling effect, in gas turbine turbine and aeromotor, be widely applied.Now rotor is no longer continuous entirety, and under multiple operating load effect, pull bar pretightning force too hour rotor can not normally connect and turn round; When pretightning force is too large, the Strength Safety deposit of stay-bolt and miscellaneous part will reduce.Determining of pull bar pretightning force size is very important problem in rod fastening rotor design always.
[summary of the invention]
The object of this invention is to provide the gas turbine pull rod rotor Prestress design check method of plane contact between a kind of wheel disc, the key parameter that it defines by control: the numerical value of bending dimensionless factor arranges suitable pull bar pretightning force, check simultaneously and reverse dimensionless factor, ensure the safe operation of gas turbine turbine wheel.
To achieve the above object of the invention, the present invention takes following technical scheme:
The gas turbine pull rod rotor Prestress design check method of plane contact between wheel disc, comprises the following steps:
1) calculate gas turbine its gravity bending moment distribution vertically in the time of static bearing supporting, obtain the suffered maximum gravity bending moment M of rotor of gas turbine
band position, the moment of torsion M transmitting while simultaneously determining gas turbine operation
t;
2) calculating rotor is subject to the cross section parameter of gravity bending moment maximum contact interface, and this cross section parameter comprises the equatorial moment of inertia I of cross section to diameter
d, second polar moment of area I
pand area of section A;
3) calculating rotor is subject to the maximum that gravity bending moment Maximum Contact interface gravity produces to throw off the compressive stress P of stress σ and pull bar pretightning force F generation
a, its formula is as follows:
σ＝M
bR
out/I
d(1)
In formula: R
outfor surface of contact external radius;
P
a＝F/A (2)
Defining bending dimensionless factor is γ
b, its formula is as follows:
γ
b＝σ/P
a(3)
Determine the numerical value of bending dimensionless factor, for actual gas turbine pull rod rotor, pull bar pretightning force F is set, make bending dimensionless factor be less than 1.0;
4) calculate rotor and be subject to the maximum shear stress τ that on gravity bending moment Maximum Contact interface, moment of torsion produces
tshearing stress τ with the lower maximum static friction force generation of pretightning force F effect
f, its formula is as follows:
τ
t＝M
tR
out/I
p(4)
τ
f＝μF/A (5)
In formula: μ is coefficient of static friction;
It is γ that dimensionless factor is reversed in definition
t: γ
t=τ
t/ τ
f(6)
Check and reverse dimensionless factor γ
tnumerical value, adjust pull bar pretightning force F, guarantee bending dimensionless factor and reverse dimensionless factor to be all less than 1.0.
Bending and torsion dimensionless factor is all less than 1.0 o'clock gas turbine pull rod rotor pretightning forces can guarantee that between wheel disc, surface of contact is not thrown off.
The present invention further improves and is, step 1) in, adopt Finite Element Method to calculate gravity bending moment, the moment of torsion M transmitting when gas turbine operation
tfor the nominal torque of gas turbine.
The present invention further improves and is, step 2) in, calculating cross section is the surface of contact between rotor disk, is subject to the wheel disc surface of contact of gravity bending moment maximum.
The present invention further improves and is, step 3) in, in the time that bending dimensionless factor is less than 1.0, between wheel disc, surface of contact contact is good; In the time that bending dimensionless factor is more than or equal to 1.0, between wheel disc, surface of contact starts to depart from.
The present invention further improves and is, step 3) in, bending dimensionless factor gets 0.1.
The present invention further improves and is, in step 4), in the time that torsion dimensionless factor is less than 1.0, between wheel disc, surface of contact contact is good; In the time that torsion dimensionless factor is more than or equal to 1.0, between wheel disc, surface of contact starts to occur slippage.
Compared with prior art, beneficial effect of the present invention is:
The present invention has defined the bending and torsion dimensionless factor of explicit physical meaning, determine the method for designing of the heavy duty gas turbine rod fastening rotor pull bar pretightning force that between wheel disc, surface of contact is plane and checked criterion, for the setting of gas turbine turbine rod fastening rotor pull bar pretightning force provides foundation, for the autonomous Design of later gas turbine lays the foundation, there is future in engineering applications widely.
[brief description of the drawings]
Fig. 1 is certain combustion machine typical structure schematic diagram;
In figure: 1,2 is bearing bearing position; 3, rotor is subject to gravity bending moment maximum position;
Fig. 2 is the process flow diagram of the gas turbine pull rod rotor Prestress design check method of plane contact between wheel disc;
Fig. 3 be between gas turbine pull rod rotor disk surface of contact at the stress distribution schematic diagram being subject under Moment;
Fig. 4 be between gas turbine pull rod rotor disk surface of contact at the shear Stress Distribution schematic diagram being subject under torsional interaction;
Fig. 5 do not consider in the situation of microcosmic Contact Effect, and the bending stiffness of rod fastening rotor surface of contact is with the variation relation schematic diagram of bending dimensionless factor.
[embodiment]
Below in conjunction with accompanying drawing, the present invention is described in further detail.
Fig. 1 is certain combustion machine typical structure schematic diagram, and bearing is generally at bearing bearing position 1 and bearing bearing position 2, and in the time that bearing supports, rotor is subject to the surface of contact of gravity bending moment maximum generally to appear at rotor and is subject to gravity bending moment maximum position 3 places.
Referring to Fig. 2 to Fig. 5, the gas turbine pull rod rotor Prestress design check method of plane contact between wheel disc of the present invention, comprises the following steps:
1) calculating of the suffered gravity bending moment of rotor of gas turbine and act on determining of moment of torsion on rotor.
The data that change along axis for obtaining comparatively accurate rotor gravity moment of flexure, generally calculate gravity bending moment by the mechanics of materials or Finite Element Method.In bearings at both ends, just prop up at place, adds gravity load, extracts the recurvation square on surface of contact between wheel disc, makes the change curve of gravity bending moment along rotor axis, finds out the surface of contact that is subject to gravity bending moment maximum.Nominal torque when acting on epitrochanterian moment of torsion and being generally rotor operation.
2) calculating of surface of contact cross section parameter.
Adopt conventional method calculation procedure 1) obtain being subject to the area of section A of gravity bending moment maximum cross-section, the equatorial moment of inertia I of cross section to diameter
d, second polar moment of area I
p.
3) maximum that gravity produces is thrown off the compressive stress of stress and the generation of pull bar pretightning force and is calculated.
Gas turbine pull rod rotor is combined wheel disc and spindle nose pretension by stay-bolt, and the drum ring texture of passing through between wheel disc connects, and contact plane is generally anchor ring.For annulus, be subject to moment M
bmake the stress distribution of used time as shown in Figure 3.Maximum stress σ=M that now moment of flexure produces on contact plane
br
out/ I
d, wherein R
outfor annulus surface of contact external radius.The compressive stress P that pull bar pretightning force F produces
a=F/A.
4) shearing stress that under the maximum shear stress that moment of torsion produces and the effect of pull bar pretightning force, maximum static friction force produces is calculated.
For the annular contact plane between gas turbine turbine wheel disc, be subject to moment of torsion M
tmake the stress distribution of used time as shown in Figure 4.The maximum shear stress τ that now moment of torsion produces on contact plane
t=M
tr
out/ I
p.The shearing stress τ that the lower maximum static friction force of pull bar pretightning force F effect produces
f=μ F/A, wherein, μ is coefficient of static friction.
5) calculate bending dimensionless factor γ
b=σ/P
a.
Its physical significance is the ratio that the maximum of gravity generation is thrown off the compressive stress of stress and the generation of pull bar pretightning force.If γ
b<1.0 represents that the suffered tearaway load of surface of contact is less than snap-in force, and surface of contact contact is good; If γ
b>=1.0 represent that the suffered tearaway load of surface of contact is greater than snap-in force, and surface of contact starts to depart from, and this situation is not allow to occur in actual moving process.Fig. 5 is the gas turbine that between certain wheel disc, surface of contact is plane, and the bending stiffness of its contact interface is with the situation of change of bending dimensionless factor.Contact interface rigidity can characterize the contact condition of contact segment intuitively.Can find out, at bending dimensionless factor γ
bwhen <1.0, surface of contact contact is good, and the rigidity of contact segment is substantially constant; At bending dimensionless factor γ
b>=1.0 o'clock, the contact stiffness of contact segment sharply declined, and showed that contact segment has started to depart from.
6) calculate and reverse dimensionless factor γ
t=τ
t/ τ
f.
Its physical significance is the ratio of the shearing stress of maximum static friction force generation under the moment of torsion maximum shear stress and the effect of pull bar pretightning force that produce.If γ
t<1.0 represents that the maximum shear stress that the suffered moment of torsion of surface of contact produces is less than the shearing stress that maximum static friction force produces, and surface of contact contact is good; If γ
t>=1.0 represent that the maximum shear stress that the suffered moment of torsion of surface of contact produces is greater than the shearing stress that maximum static friction force produces, and surface of contact starts to occur slippage, and this situation is not allow to occur in actual moving process.Reversing dimensionless factor γ
twhen <1.0, surface of contact contact is good, and the torsional rigidity of contact segment is substantially constant; Reversing dimensionless factor γ
t>=1.0 o'clock, the torsion contact stiffness of contact segment sharply declined, and showed that surface of contact has started to occur slippage.
7) according to bending dimensionless factor γ
bthrow off stress σ with maximum, draw required design pull bar pretightning force value: F=A σ/γ
b;
Bending dimensionless factor γ
bmust be less than 1.0, for ensure that enough safety allowances make the unlikely disengagement of surface of contact take into account the margin of safety of rotor, bending dimensionless factor γ simultaneously
bgenerally get 0.1.
8) check the numerical value that reverses dimensionless factor, at least need to ensure to reverse dimensionless factor γ
tbe less than 1.0.For ensureing that security needs leave certain safety allowance.
Claims (6)
1. the gas turbine pull rod rotor Prestress design check method of plane contact between wheel disc, is characterized in that, comprises the following steps:
1) calculate gas turbine its gravity bending moment distribution vertically in the time of static bearing supporting, obtain the suffered maximum gravity bending moment M of rotor of gas turbine
band position, the moment of torsion M transmitting while simultaneously determining gas turbine operation
t;
2) calculating rotor is subject to the cross section parameter of gravity bending moment maximum contact interface, and this cross section parameter comprises the equatorial moment of inertia I of cross section to diameter
d, second polar moment of area I
pand area of section A;
3) calculating rotor is subject to the maximum that gravity bending moment Maximum Contact interface gravity produces to throw off the compressive stress P of stress σ and pull bar pretightning force F generation
a, its formula is as follows:
σ＝M
bR
out/I
d(1)
In formula: R
outfor surface of contact external radius;
P
a＝F/A (2)
Defining bending dimensionless factor is γ
b, its formula is as follows:
γ
b＝σ/P
a(3)
Determine the numerical value of bending dimensionless factor, for actual gas turbine pull rod rotor, pull bar pretightning force F is set, make bending dimensionless factor be less than 1.0;
4) calculate rotor and be subject to the maximum shear stress τ that on gravity bending moment Maximum Contact interface, moment of torsion produces
tshearing stress τ with the lower maximum static friction force generation of pretightning force F effect
f, its formula is as follows:
τ
t＝M
tR
out/I
p(4)
τ
f＝μF/A (5)
In formula: μ is coefficient of static friction;
It is γ that dimensionless factor is reversed in definition
t: γ
t=τ
t/ τ
f(6)
Check and reverse dimensionless factor γ
tnumerical value, adjust pull bar pretightning force F, guarantee bending dimensionless factor and reverse dimensionless factor to be all less than 1.0;
In the time that bending and torsion dimensionless factor is all less than 1.0, gas turbine pull rod rotor pretightning force can guarantee that between wheel disc, surface of contact is not thrown off.
2. the gas turbine pull rod rotor Prestress design check method of plane contact between wheel disc according to claim 1, is characterized in that step 1) in, adopt Finite Element Method to calculate gravity bending moment, the moment of torsion M transmitting when gas turbine operation
tfor the nominal torque of gas turbine.
3. the gas turbine pull rod rotor Prestress design check method of plane contact between wheel disc according to claim 1, is characterized in that step 2) in, calculating cross section is the surface of contact between rotor disk, is subject to the wheel disc surface of contact of gravity bending moment maximum.
4. the gas turbine pull rod rotor Prestress design check method of plane contact between wheel disc according to claim 1, is characterized in that step 3) in, in the time that bending dimensionless factor is less than 1.0, between wheel disc, surface of contact contact is good; In the time that bending dimensionless factor is more than or equal to 1.0, between wheel disc, surface of contact starts to depart from.
5. according to the gas turbine pull rod rotor Prestress design check method of plane contact between the wheel disc described in claim 1 or 4, it is characterized in that, bending dimensionless factor gets 0.1.
6. the gas turbine pull rod rotor Prestress design check method of plane contact between wheel disc according to claim 1, is characterized in that, in step 4), in the time that torsion dimensionless factor is less than 1.0, between wheel disc, surface of contact contact is good; In the time that torsion dimensionless factor is more than or equal to 1.0, between wheel disc, surface of contact starts to occur slippage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410178520.1A CN103970944B (en) | 2014-04-29 | 2014-04-29 | Design and check method for pre-tightening force of rod fastening rotor of gas turbine with wheel disks in plane contact |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410178520.1A CN103970944B (en) | 2014-04-29 | 2014-04-29 | Design and check method for pre-tightening force of rod fastening rotor of gas turbine with wheel disks in plane contact |
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| Publication Number | Publication Date |
|---|---|
| CN103970944A true CN103970944A (en) | 2014-08-06 |
| CN103970944B CN103970944B (en) | 2017-04-26 |
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|---|---|---|---|
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105736059A (en) * | 2016-02-01 | 2016-07-06 | 西安交通大学 | High-speed dynamic balance ability optimization design method for gas turbine pull rod rotor with end face teeth |
| CN106295045A (en) * | 2016-08-18 | 2017-01-04 | 西安交通大学 | Identify partial disengagement position, rod fastening rotor interface and the generalized flexibility matrix method of degree |
| CN107131993A (en) * | 2017-07-05 | 2017-09-05 | 上海应用技术大学 | The scaling method and calibration system of a kind of circumferential rod fastening rotor pull bar pretightning force of disc type |
| CN107895077A (en) * | 2017-11-10 | 2018-04-10 | 西安交通大学 | Consider that disk rouses the gas turbine pull rod rotor assembly parameter optimization method of more manufacture factors |
| CN111473928A (en) * | 2020-03-23 | 2020-07-31 | 中国科学院工程热物理研究所 | Method for calculating bending stiffness of contact interface of gas turbine pull rod rotor |
-
2014
- 2014-04-29 CN CN201410178520.1A patent/CN103970944B/en not_active Expired - Fee Related
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105736059A (en) * | 2016-02-01 | 2016-07-06 | 西安交通大学 | High-speed dynamic balance ability optimization design method for gas turbine pull rod rotor with end face teeth |
| CN105736059B (en) * | 2016-02-01 | 2017-04-26 | 西安交通大学 | High-speed dynamic balance ability optimization design method for gas turbine pull rod rotor with end face teeth |
| CN106295045A (en) * | 2016-08-18 | 2017-01-04 | 西安交通大学 | Identify partial disengagement position, rod fastening rotor interface and the generalized flexibility matrix method of degree |
| CN106295045B (en) * | 2016-08-18 | 2019-07-23 | 西安交通大学 | Identify the generalized flexibility matrix method of rod fastening rotor interface partial disengagement position and degree |
| CN107131993A (en) * | 2017-07-05 | 2017-09-05 | 上海应用技术大学 | The scaling method and calibration system of a kind of circumferential rod fastening rotor pull bar pretightning force of disc type |
| CN107895077A (en) * | 2017-11-10 | 2018-04-10 | 西安交通大学 | Consider that disk rouses the gas turbine pull rod rotor assembly parameter optimization method of more manufacture factors |
| 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 |
| CN111473928A (en) * | 2020-03-23 | 2020-07-31 | 中国科学院工程热物理研究所 | Method for calculating bending stiffness of contact interface of gas turbine pull rod rotor |
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