CN101825115B - Blade with built-in bed frame-type pneumatic damping device - Google Patents
Blade with built-in bed frame-type pneumatic damping device Download PDFInfo
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- CN101825115B CN101825115B CN2010101392346A CN201010139234A CN101825115B CN 101825115 B CN101825115 B CN 101825115B CN 2010101392346 A CN2010101392346 A CN 2010101392346A CN 201010139234 A CN201010139234 A CN 201010139234A CN 101825115 B CN101825115 B CN 101825115B
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Abstract
The invention discloses a blade structure with a built-in bed frame-type pneumatic damping device; a blade comprises a blade body and a tennon, wherein the blade body comprises a blade back side wall, a blade basin side wall, a front edge, a rear edge, an A shock-absorbing plate, a B shock-absorbing plate, a C shock-absorbing plate, an A support rib and a B support rib; the blade back side wall and the blade basin side wall are arranged between the front edge and the rear edge, and a runner is arranged between the blade back side wall and the blade basin side wall; the B shock-absorbing plate is arranged between the A support rib and the B support rib, the A shock-absorbing plate is arranged in an installation groove on the other side of the A support rib, the C shock-absorbing plate is arranged in the installation groove on the other side of the B support rib, so as to form a frame-type pneumatic damping structure; and the frame-type pneumatic damping structure is arranged in the runner which is formed by the blade back side wall and the blade basin side wall. The design of the blade structure can absorb the vibration energy of a blade body wing surface within a very wide frequency domain range, reduce the vibration stress level of the blade body, so as to solve the problem of the high-cycle fatigue failure of the blade caused by the intensive mode of the blade and the failure to avoid resonance.
Description
Technical field
The present invention relates to a kind of high speed rotating gas turbine blades that is used for, more particularly say, be meant a kind of blade structure of built-in bed frame-type pneumatic damping device.
Background technique
Along with the develop rapidly of aeronautical technology, the new technology that big Bypass Ratio Turbofan Engine adopts is also in continuous increase, and wide string fan blade is exactly one of key technology wherein.We can say that to a certain extent whether succeeding in developing of wide string fan blade determines big bypass ratio Duct-Burning Turbofan possibility of success.Wide string fan blade has increases compressor surge nargin, efficient height, anti-foreign object damage, improve motor power, reduce advantages such as the number of blade and weight reduction, and advanced fan rotor blade is curved plunders design possibility is provided in order to adopt.
Early stage fan blade is mainly used the titanium alloy material manufacturing, and the damping convex shoulder that stretches out apart from oriented both sides, blade tip 1/3rd places at blade pushes against stiffening ring of formation mutually between blade.This design can increase the blade rigid and the natural frequency of vibration to a certain extent, and when blade vibration, the relative movement of adjacent blades convex shoulder surface of contact produces frictional damping, reduces the vibration stress of blade.But air flow stream is crossed the convex shoulder place can produce separation, air-flow efficient is reduced, and solid vane weight is excessive, and the wheel disc load is excessive.Shouldered solid fan blade can not adapt to the performance requirement of high thrust motor to fan blade fully.
At the shortcoming that the solid fan blade of early stage narrow string exists, Luo-Luo company has at first succeeded in developing the wide string fan blade of the first generation in the eighties.It fuses titanium plate and an interior thin-walled honeycomb central layer of two hot blade shapes with activation or liquid state diffusion welding process, makes wide string and does not have the convex shoulder fan blade.The nineties, Luo-Luo company was on the basis of the wide string blade of first generation honeycomb core plate, success adopt the fan blade that superplastic forming/diffusion connection (SPF/DB) group technology is made of titanium alloy three-decker, the fan blade core adopts architectural used triangular truss structure, the inside honeycomb core plate of wide string fan blade before having replaced.This triangular truss structure is lightweight not only, and can load, and every leaf weight is lighter by 1% than honeycomb core blade.U.S. Pu Hui company is at the PW40 of development and production same period series turbofan engine, and wide beam string structure is also adopted in the design of fan blade.
Compare with the solid band convex shoulder of early stage narrow string fan blade, wide string does not have the convex shoulder fan blade and have following characteristics on structural design: 1) save convex shoulder, reduced the profile drag and the pressure loss, improve air dynamic behaviour; 2) increase chord length, improved the anti-foreign object ability of injuring; 3) adopt hollow-core construction, alleviated leaf weight greatly.Yet this novel fan blade has lost the design of traditional convex shoulder, and himself damper mechanism of blade has only the mechanical damping of blade material and internal structure thereof, and the blade high cycles fatigue that is not enough to avoid effectively causing because of forced vibration lost efficacy.While improving constantly along with engine performance, the airload that blade bore also constantly increases, the pneumatic design of high load makes the high cycles fatigue inefficacy that is caused by the blade high frequent vibration frequently take place, and hardly may and attempt to avoid the intensive high-order resonant frequency in each rank.Therefore must seek the anti-high cycles fatigue damage that various new structures improve fan blade, prolong fan blade fatigue life.
Summary of the invention
For intensity, vibration characteristics and the life-span of improving blade, the present invention has designed a kind of blade structure of built-in bed frame-type pneumatic damping device.This blade is to be made of blade and tenon.When blade is subjected to aerodynamic loading excitation generation vibration, vibrational energy on the blade aerofoil (blade back sidewall and leaf basin sidewall) is absorbed by the absorbing plate of blade inside, the relative movement that vibration causes inner six the air cavity upper and lower surfaces of blade takes place in the absorbing plate, makes the interior gas of air cavity take place to flow.Because gas has viscosity, near solid wall surface, can there be boundary layer during gas flow, there is viscous shearing stress in gas flow speed and inhomogeneous in the boundary layer, can cause flow losses for overcoming the merit that these viscous forces do, and consumes vibrational energy.While is owing to the existence of throttle orifice on the absorbing plate, during the gas flow throttle orifice, because aisle spare reduces suddenly to cause flowing velocity acutely to increase, the air current flow direction changes, and fluid particle clashes into mutually, and violent friction and momentum transfer take place, cause energy loss, consume vibrational energy.The existence of pneumatic damping has reduced the vibration stress of blade, has improved the high cycles fatigue life-span of blade.
The blade of the built-in bed frame-type pneumatic damping device of the present invention's design is made of blade and tenon, and wherein, blade includes blade back sidewall, leaf basin sidewall, leading edge, trailing edge, A absorbing plate, B absorbing plate, C absorbing plate, A ribs and B ribs.Blade back sidewall and leaf basin sidewall are oppositely arranged between leading edge and the trailing edge, and form a runner cavity between blade back sidewall and the leaf basin sidewall; B absorbing plate is installed between A ribs and the B ribs, and A absorbing plate is installed in the mounting groove of the opposite side of A ribs, and C absorbing plate is installed in the mounting groove of the opposite side of B ribs, thereby forms the bed frame-type pneumatic damping device structure; This bed frame-type pneumatic damping device structure is installed in the runner cavity of blade back sidewall and the formation of leaf basin sidewall, and makes runner cavity internal insulation become six air cavitys by A ribs and B ribs.The blade profile of described blade is designed to have certain torsional angle β=20 °～40 °.
The blade with built-in bed frame-type pneumatic damping device of the present invention's design has following advantage:
(1) design of bed frame-type absorbing plate structure can absorb the vibrational energy of blade blade aerofoil in 2000Hz～12000Hz frequency domain scope, reduce the vibration stress level of blade, thereby solved the blade high cycles fatigue Problem of Failure that to avoid resonating and be caused because blade mode is intensive.
(2) design of ribs has improved the impact resistance of blade effectively in the bed frame-type absorbing plate structure.
(3) introduce gas in the blade cavity, the pneumatic damping that gas flow produced can effectively suppress the dither of blade, does not increase the weight of blade simultaneously, meets the loss of weight requirement of modern motor.
(4) blade air cavity structure Design makes gas produce along the journey energy loss in the existence of flow process owing to boundary layer, and the design of throttle orifice can also increase the local energy loss that gas produces owing to the sudden change of air-flow path on the absorbing plate in flow process.Air cavity that bed frame-type absorbing plate and front and rear edge form and the throttle orifice on the absorbing plate have all increased the pneumatic damping in the blade cavity dramatically, suppress the vibration of absorbing plate structure effectively, avoided absorbing panel vibration stress excessive and the high cycles fatigue that causes lost efficacy.
Description of drawings
Fig. 1 is the main perspective degree structural drawing of blade of the present invention.
Figure 1A is the backsight angle structural drawing of blade of the present invention.
Figure 1B is the depression angle structural drawing of blade of the present invention.
Fig. 1 C is the exploded view of blade of the present invention.
Fig. 1 D is the erection drawing with blade of the present invention and blades.
Fig. 2 is the structural drawing of blade tenon of the present invention.
Fig. 3 is the structural drawing of blade and blade back side wall of the present invention.
Fig. 4 is the structural drawing of blade and blade basin sidewall of the present invention.
Fig. 5 is the structural drawing of blade inlet edge of the present invention.
Fig. 6 is the structural drawing of trailing edge of the present invention.
Fig. 7 is the structural drawing of blade A ribs of the present invention.
Fig. 8 is the structural drawing of blade B ribs of the present invention.
Fig. 9 is the effectiveness in vibration suppression comparison diagram of blade of the present invention and traditional blades.
Among the figure: 1. 102. lower ends, blade back sidewall 101. upper ends, 2. leaf basin sidewalls
201. 202. lower ends, upper end, 3. tenons, 31. runners, 32. base plate faces
33. 402. lower ends, draw-in groove 34. slot 4. leading edges, 401. upper ends
403. connecting end 404. arc tips 405. chamferings 5. trailing edges 501. upper ends
502. lower end 503. connecting ends, 504. arc tips, 505. chamfering 11.A absorbing plates
A throttle orifice 113 12.B absorbing plate B throttle orifices 123 13.C absorbing plate C throttle orifices 133
21.A ribs 211. upper ends 212. lower end 213.A mounting groove 214.B mounting grooves
22.B ribs 221. upper ends 222. lower end 223.C mounting groove 224.D mounting grooves
111.A air cavity 112.B air cavity 121.C air cavity 122.D air cavity 131.E air cavity
132.F the air cavity 1A. first blade 1B. wheel disc 1C. tongue-and-groove 1D. blades
1E. outer flow passage 1F. second blade
Embodiment
The present invention is described in further detail below in conjunction with accompanying drawing.
Shown in Fig. 1, Figure 1A, Figure 1B and Fig. 1 C, the blade of a kind of built-in bed frame-type pneumatic damping device of the present invention is to be made of blade and tenon 3, wherein, blade includes blade back sidewall 1, leaf basin sidewall 2, leading edge 4, trailing edge 5, A absorbing plate 11, B absorbing plate 12, C absorbing plate 13, A ribs 21 and B ribs 22.
In Figure 1B, the A point is the central point of the arc tips of leading edge 4 upper ends, and the B point is the central point of the arc tips of trailing edge 5 upper ends, and the line that connection A point and B are ordered is called the AB line, and the AB line just in time also is the middle string of a musical instrument of blade of the present invention; The C point is the central point of leaf basin sidewall 2 upper ends, and the D point is the central point of blade back sidewall 1 upper end, and the line that connection C point and D are ordered claims CD line (also being the neutrality line of blade); The intersection point of AB line and CD line is O, and OC=OD.
Referring to shown in Figure 3, blade back sidewall 1 is one and has the certain torsional angle β (β=20 °～40 °) and the first bent angle θ
1Shell.In the present invention, in order to prevent that gas separates at boundary layer in the outer flow passage 1E, the first bent angle θ then
1Scope should satisfy
θ
1minRepresent the first bent angle θ
1Get the minimum angles value, θ
1maxRepresent the first bent angle θ
1Get maximal angle value.Described outer flow passage 1E (shown in Fig. 1 D) is meant the passage between adjacent two blades (can be the first blade 1A and the second blade 1F).
Referring to shown in Figure 4, leaf basin sidewall 2 is one and has the certain torsional angle β (β=20 °～40 °) and the second bent angle θ
2Shell.In the present invention, in order to prevent that gas separates at boundary layer in the outer flow passage 1E, the second bent angle θ then
2Scope should satisfy
θ
2minRepresent the second bent angle θ
2Get the minimum angles value, θ
2maxRepresent the second bent angle θ
2Get maximal angle value.
Referring to shown in Figure 2, tenon 3 is provided with runner 31, and an end of the base plate face 32 of tenon 3 is provided with slot 34, and the other end is provided with draw-in groove 33.Blade is installed in the runner 31, and while runner 31 is used for high-speed gas to be passed through.In the present invention, blade pass is crossed tenon 3 and is installed on the blades 1D, and draw-in groove 33 and slot 34 are used to realize the axially locating of blade.
Referring to shown in Figure 5, leading edge 4 is the wedge-shaped blockss with certain torsional angle β (β=20 °～40 °) and arc tips 404.In the present invention, for satisfying requirement of strength, the lower end 402 of connecting end 403 from the upper end 401 of leading edge 4 to leading edge 4 is provided with chamfering 405, and the radius of the arc tips 404 of leading edge 4 is designated as r
4, r
4Satisfy 0.1852 * L, L represents the length of CD line.
Referring to shown in Figure 6, trailing edge 5 is the wedge-shaped blockss with certain torsional angle β (β=20 °～40 °) and arc tips 504.In the present invention, for satisfying requirement of strength, the lower end 502 of connecting end 503 from the upper end 501 of trailing edge 5 to trailing edge 5 is provided with chamfering 505, and the radius of the arc tips 504 of trailing edge 5 is designated as r
5, r
5Satisfy 0.197 * L, L represents the length of CD line.
Referring to shown in Figure 7, A ribs 21 is a structural I-beam with certain torsional angle β (β=20 °～40 °), A mounting groove 213 that A ribs 21 is provided with and B mounting groove 214; One sidewall of A absorbing plate 11 is installed in the A mounting groove 213, and another sidewall of A absorbing plate 11 is installed on the trailing edge 5; One sidewall of B absorbing plate 12 is installed in the B mounting groove 214, and another sidewall of B absorbing plate 12 is installed in the C mounting groove 223 of B ribs 22.
Referring to shown in Figure 8, B ribs 22 is a structural I-beam with certain torsional angle β (β=20 °～40 °), C mounting groove 223 that B ribs 22 is provided with and D mounting groove 224; Another sidewall of B absorbing plate 12 is installed in the C mounting groove 223; One sidewall of C absorbing plate 13 is installed in the D mounting groove 224, and another sidewall of C absorbing plate 13 is installed on the leading edge 4.In the present invention, A ribs 21 is identical with the structure of B ribs 22.Strengthening rib plays support frame, keeps blade profile, forms air-flow path and the fixedly effect of absorbing plate.Referring to shown in Figure 2, A absorbing plate 11 is the thin plates with certain torsional angle β (β=20 °～40 °), and A absorbing plate 11 is according to the damping ratio of A absorbing plate 11
Carry out the setting of A throttle orifice 113.
The damping ratio of A absorbing plate 11
Wherein,
K (ε)=4 ε
2-ε
4-4ln ε-3,
μ represents the gas viscosity damping constant; A
11Surface area (length * wide=the L of expression A absorbing plate 11
A* L
B); H
11The thickness of expression A absorbing plate 11; r
11The radius of expression A throttle orifice 113; r
aHalf of hole heart distance of representing adjacent two A throttle orifices 113; ρ
11The density of expression A absorbing plate 11 selected materials; E
11The Young's modulus of expression A absorbing plate 11 selected materials.
Referring to shown in Figure 2, B absorbing plate 12 is the thin plates with certain torsional angle β (β=20 °～40 °), and B absorbing plate 12 is according to the damping ratio of B absorbing plate 12
Carry out the setting of B throttle orifice 123.
The damping ratio of B absorbing plate 12
Wherein,
K (ε)=4 ε
2-ε
4-4ln ε-3,
μ represents the gas viscosity damping constant; A
12The surface area of expression B absorbing plate 12; H
12The thickness of expression B absorbing plate 12; r
12The radius of expression B throttle orifice 123; r
bHalf of hole heart distance of representing adjacent two B throttle orifices 123; ρ
12The density of expression B absorbing plate 12 selected materials; E
12The Young's modulus of expression B absorbing plate 12 selected materials.
Referring to shown in Figure 2, C absorbing plate 13 is the thin plates with certain torsional angle β (β=20 °～40 °), and C absorbing plate 13 is according to the damping ratio of C absorbing plate 13
Carry out the setting of C throttle orifice 133.
The damping ratio of C absorbing plate 13
Wherein,
K (ε)=4 ε
2-ε
4-4ln ε-3,
μ represents the gas viscosity damping constant; A
13The surface area of expression C absorbing plate 13; H
13The thickness of expression C absorbing plate 13; r
11The radius of expression C throttle orifice 133; r
cHalf of hole heart distance of representing adjacent two C throttle orifices 133; ρ
13The density of expression C absorbing plate 13 selected materials; E
13The Young's modulus of expression C absorbing plate 13 selected materials.
In the present invention, the diameter and the distribution density (throttling distance between borehole) of the throttle orifice that is provided with on three absorbing plates are the major parameters of its design.If the diameter of throttle orifice is excessive, then there is too many gas from throttle orifice, to flow out inflow, will reduce along the journey flow losses because of the flowing velocity that reduces intracavity gas.If the diameter of throttle orifice is too small, then can not obtain good local pneumatic damping.Therefore by the throttle orifice diameter being set and the throttling distance between borehole can obtain better pneumatic damping.If the natural frequency of A absorbing plate 11, B absorbing plate 12 and C absorbing plate 13 is ω
s, the blade natural frequency is ω
b, then have the physical dimension design of described three absorbing plates should satisfy frequency ratio
Should be as far as possible near 1 designing requirement.
Being assembled into of the blade with built-in bed frame-type pneumatic damping device of the present invention's design:
Blade back sidewall 1 is staggered relatively with leaf basin sidewall 2, and leading edge 4 is staggered relatively with trailing edge 5, then blade back sidewall 1 and leaf basin sidewall 2 is installed between leading edge 4 and the trailing edge 5, and forms a runner cavity between blade back sidewall 1 and the leaf basin sidewall 2.
Three blocks of absorbing plates are connected to form the bed frame-type pneumatic damping device structure by two ribs respectively, and this bed frame-type pneumatic damping device structure places described runner cavity.The both sides that are B absorbing plate 12 are installed in the mounting groove of A ribs 21 and B ribs 22, A absorbing plate 11 is installed in the mounting groove of the opposite side of A ribs 21, C absorbing plate 13 is installed in the mounting groove of the opposite side of B ribs 22, thereby forms the bed frame-type pneumatic damping device structure.The blade of the present invention design is the requirement of satisfying the aeroperformance amount of work, and the blade profile of blade has certain torsional angle β, and torsional angle β=20 °～40 °.
Described runner cavity is separated into six air cavitys by described bed frame-type pneumatic damping device structure, i.e. between A absorbing plate 11 and the blade back sidewall 1 A air cavity 111 is arranged, and between A absorbing plate 11 and the leaf basin sidewall 2 B air cavity 112 is arranged; Between B absorbing plate 12 and the blade back sidewall 1 C air cavity 121 is arranged, between B absorbing plate 12 and the leaf basin sidewall 2 D air cavity 122 is arranged; Between C absorbing plate 13 and the blade back sidewall 1 E air cavity 131 is arranged, between C absorbing plate 13 and the leaf basin sidewall 2 F air cavity 132 is arranged; Above-mentioned six air cavitys can make the air-flow that enters form along the journey damping structure, cooperating of throttle orifice have formed the Local Damping structure on per two air cavitys and separately the absorbing plate.At each Local Damping structure in detail, A air cavity 111 and B air cavity 112 with cooperating of A throttle orifice 113 form first Local Damping structure on the A absorbing plate 11; Cooperating of B throttle orifice 123 on C air cavity 121 and D air cavity 122 and the B absorbing plate 12 forms second Local Damping structure; E air cavity 131 and F air cavity 132 with cooperating of C throttle orifice 133 form the 3rd Local Damping structure on the C absorbing plate 13.
Shown in Fig. 1 D, the blade installation of the present invention design on blades 1D, is promptly installed between 3, two blades of vaned tenon (the first blade 1A, the second blade 1F) in the tongue-and-groove 1C between per two wheel disc 1B of blades 1D and had outer flow passage 1E.
In order to verify the blade structure that the present invention designs and the effectiveness in vibration suppression of traditional blades structure, Fig. 9 has provided the vibration displacement frequency domain figure of traditional blades and blade of the present invention, by finding out among the figure, in 2000Hz～12000Hz frequency domain scope, the vibration displacement of the blade structure of bed frame-type pneumatic damping device of the present invention has good vibration suppressioning effect much smaller than traditional blades.
The blade structure of a kind of built-in bed frame-type pneumatic damping device provided by the invention, when blade was subjected to aerodynamic loading excitation generation vibration, the vibrational energy on the blade sidewall was absorbed by the absorbing plate of inside, and the absorbing panel vibration causes gas flow in the air cavity.Be to overcome the interior viscous shearing stress of boundary layer and work done, the consumption vibrational energy during gas flow.Many absorbings plate structure design of bed frame-type can absorb the vibrational energy of blade blade aerofoil in very wide frequency domain scope, reduce the vibration stress level of blade, thereby solved the blade high cycles fatigue Problem of Failure that to avoid resonating and be caused because blade mode is intensive; The design of many air cavitys structure and throttle orifice makes gas produce simultaneously along journey energy loss and local energy loss at flow process, increased the pneumatic damping in the blade cavity dramatically, thereby suppress the vibration of absorbing plate structure effectively, avoided absorbing panel vibration stress excessive and the high cycles fatigue that causes lost efficacy.The blade structure of a kind of built-in bed frame-type pneumatic damping device provided by the invention when effectively suppressing the dither of blade, does not increase the weight of blade, meets the requirement of modern motor high-performance, high thrust weight ratio.
Claims (2)
1. the blade of a built-in bed frame-type pneumatic damping device, it is characterized in that: this blade is to be made of blade and tenon (3), wherein, blade includes blade back sidewall (1), leaf basin sidewall (2), leading edge (4), trailing edge (5), A absorbing plate (11), B absorbing plate (12), C absorbing plate (13), A ribs (21) and B ribs (22); A ribs (21) is identical with the structure of B ribs (22);
Blade back sidewall (1) is one and has certain torsional angle β=20 °～40 ° and first bent angle θ
1Shell; The first bent angle θ
1Scope should satisfy
θ
1minRepresent the first bent angle θ
1Get the minimum angles value, θ
1maxRepresent the first bent angle θ
1Get maximal angle value;
Leaf basin sidewall (2) is one and has certain torsional angle β=20 °～40 ° and second bent angle θ
2Shell; The second bent angle θ
2Scope should satisfy
θ
2minRepresent the second bent angle θ
2Get the minimum angles value, θ
2maxRepresent the second bent angle θ
2Get maximal angle value;
Tenon (3) is provided with runner (31), and an end of the base plate face (32) of tenon (3) is provided with slot (34), and the other end is provided with draw-in groove (33);
Leading edge (4) is a wedge-shaped blocks with certain torsional angle β=20 °～40 ° and arc tips (404); The radius r of described arc tips (404)
4Satisfy 0.1852 * L, L represents the length of CD line, and the CD line is the neutrality line of blade;
Trailing edge (5) is a wedge-shaped blocks with certain torsional angle β=20 °～40 ° and arc tips (504); The radius r of described arc tips (504)
5Satisfy 0.197 * L, L represents the length of CD line, and the CD line is the neutrality line of blade;
A ribs (21) is a structural I-beam with certain torsional angle β=20 °～40 °, and a sidewall of A absorbing plate (11) is installed in the A mounting groove (213) of A ribs (21), and another sidewall of A absorbing plate (11) is installed on the trailing edge (5); One sidewall of B absorbing plate (12) is installed in the B mounting groove (214) that A ribs (21) is provided with, and another sidewall of B absorbing plate (12) is installed in the C mounting groove (223) of B ribs (22);
B ribs (22) is a structural I-beam with certain torsional angle β=20 °～40 °, and another sidewall of B absorbing plate (12) is installed in the C mounting groove (223) of B ribs (22); One sidewall of C absorbing plate (13) is installed in the D mounting groove (224) that B ribs (22) is provided with, and another sidewall of C absorbing plate (13) is installed on the leading edge (4); A absorbing plate (11) is a thin plate with certain torsional angle β=20 °～40 °, and A absorbing plate (11) is according to the damping ratio of A absorbing plate
Carry out the setting of A throttle orifice (113); The damping ratio of A absorbing plate
Wherein,
K (ε)=4 ε
2-ε
4-4ln ε-3,
μ represents the gas viscosity damping constant; A
11The surface area of expression A absorbing plate (11); H
11The thickness of expression A absorbing plate (11); r
11The radius of expression A throttle orifice (113); r
aHalf of hole heart distance of representing adjacent two A throttle orifices (113); ρ
11The density of the selected material of expression A absorbing plate (11); E
11The Young's modulus of the selected material of expression A absorbing plate (11);
B absorbing plate (12) is a thin plate with certain torsional angle β=20 °～40 °, and B absorbing plate (12) is according to the damping ratio of B absorbing plate
Carry out the setting of B throttle orifice (123); The damping ratio of B absorbing plate
Wherein,
K (ε)=4 ε
2-ε
4-4ln ε-3,
μ represents the gas viscosity damping constant; A
12The surface area of expression B absorbing plate (12); H
12The thickness of expression B absorbing plate (12); r
12The radius of expression B throttle orifice (123); r
bHalf of hole heart distance of representing adjacent two B throttle orifices (123); ρ
12The density of the selected material of expression B absorbing plate (12); E
12The Young's modulus of the selected material of expression B absorbing plate (12);
C absorbing plate (13) is a thin plate with certain torsional angle β=20 °～40 °, and C absorbing plate (13) is according to the damping ratio of C absorbing plate
Carry out the setting of C throttle orifice (133); The damping ratio of C absorbing plate
Wherein,
K (ε)=4 ε
2-ε
4-4ln ε-3,
μ represents the gas viscosity damping constant; A
13The surface area of expression C absorbing plate (13); H
13The thickness of expression C absorbing plate (13); r
13The radius of expression C throttle orifice (133); r
cHalf of hole heart distance of representing adjacent two C throttle orifices (133); ρ
13The density of the selected material of expression C absorbing plate (13); E
13The Young's modulus of the selected material of expression C absorbing plate (13);
Blade back sidewall (1) is staggered relatively with leaf basin sidewall (2), leading edge (4) is staggered relatively with trailing edge (5), then blade back sidewall (1) and leaf basin sidewall (2) are installed between leading edge (4) and the trailing edge (5), and form a runner cavity between blade back sidewall (1) and the leaf basin sidewall (2); Three blocks of absorbing plates are connected to form the bed frame-type pneumatic damping device structure by two ribs respectively; Place described runner cavity to assemble the blade that has constituted blade described bed frame-type pneumatic damping device structure; Described blade is installed in the runner (31) of tenon (3);
Described runner cavity is separated into six air cavitys by described bed frame-type pneumatic damping device structure, i.e. between A absorbing plate (11) and the blade back sidewall (1) A air cavity (111) is arranged, and between A absorbing plate (11) and the leaf basin sidewall (2) B air cavity (112) is arranged; Between B absorbing plate (12) and the blade back sidewall (1) C air cavity (121) is arranged, between B absorbing plate (12) and the leaf basin sidewall (2) D air cavity (122) is arranged; Between C absorbing plate (13) and the blade back sidewall (1) E air cavity (131) is arranged, between C absorbing plate (13) and the leaf basin sidewall (2) F air cavity (132) is arranged; A air cavity (111) and B air cavity (112) with cooperating of A throttle orifice (113) form first Local Damping structure on the A absorbing plate (11); Cooperating of B throttle orifice (123) on C air cavity (121) and D air cavity (122) and the B absorbing plate (12) forms second Local Damping structure; E air cavity (131) and F air cavity (132) with cooperating of C throttle orifice (133) form the 3rd Local Damping structure on the C absorbing plate (13).
2. the blade of built-in bed frame-type pneumatic damping device according to claim 1, it is characterized in that: the natural frequency of A absorbing plate (11), B absorbing plate (12) and C absorbing plate (13) is ω
s, the blade natural frequency is ω
b, then have the physical dimension design of described three absorbing plates should satisfy frequency ratio
Should be as far as possible near 1 designing requirement.
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| CN2010101392346A CN101825115B (en) | 2010-03-31 | 2010-03-31 | Blade with built-in bed frame-type pneumatic damping device |
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|---|---|---|---|
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| CN101825115B true CN101825115B (en) | 2011-09-28 |
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| CN108661948B (en) * | 2018-04-28 | 2019-12-13 | 中国民航大学 | Air film damping fan blade with throttling hole covered vibration absorption thin plate |
| CN112443360B (en) * | 2019-08-29 | 2022-09-27 | 香港城市大学深圳研究院 | Aeroengine blade and aeroengine |
| CN110514378B (en) * | 2019-08-30 | 2021-11-30 | 中国航发动力股份有限公司 | Vibration fatigue test device for fan blade with convex shoulder of engine |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3854842A (en) * | 1973-04-30 | 1974-12-17 | Gen Electric | Rotor blade having improved tip cap |
| GB1508571A (en) * | 1973-10-13 | 1978-04-26 | Rolls Royce | Hollow cooled blade or vane for a gas turbine engine |
| IN163070B (en) * | 1984-11-15 | 1988-08-06 | Westinghouse Electric Corp | |
| US6695582B2 (en) * | 2002-06-06 | 2004-02-24 | General Electric Company | Turbine blade wall cooling apparatus and method of fabrication |
| US6742991B2 (en) * | 2002-07-11 | 2004-06-01 | Mitsubishi Heavy Industries, Ltd. | Turbine blade and gas turbine |
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| CN101825115A (en) | 2010-09-08 |
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