CN204627758U - Sealing component and gas turbine - Google Patents
Sealing component and gas turbine Download PDFInfo
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- CN204627758U CN204627758U CN201520176997.6U CN201520176997U CN204627758U CN 204627758 U CN204627758 U CN 204627758U CN 201520176997 U CN201520176997 U CN 201520176997U CN 204627758 U CN204627758 U CN 204627758U
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Abstract
The utility model relates to a kind of sealing component and gas turbine, and sealing component possesses: the first engagement portion (8), and it is arranged on the axial upstream side of rotor, and is connected with the end in the described axial downstream side of tail pipe (21); Second engagement portion (9), it is arranged on described axial downstream side, and with chimeric with the protuberance (452) of guard shield (45) in described axially overlapping mode.Second engagement portion (9) is formed with the recess (94b) caved in the radial direction of described rotor shaft in the end in the described axial downstream side of opposed faces (93a), this recess (94b) is provided with the elastomer seal (95) in blocking this recess and the gap between opposed protuberance (452).Recess (94b) is formed in the mode that local extends in the circumferential.
Description
Technical field
The utility model relates to a kind of sealing component and gas turbine.
Background technique
In the gas turbine, the air made by compressor pressurizes produces the combustion gas of the fluid as high temperature in the burner with fuel mix, and by these combustion gas to be alternately equipped stator blade and moving vane turbine combustion gas stream in import.By the combustion gas circulated in combustion gas stream, moving vane and rotor are rotated, thus the energy of combustion gas is exported as rotating energy and gives rotary driving force to compressor, generator.
Between the tail pipe of burner and the guard shield of the first stage stator blades sheet of turbine, be provided with gap to prevent the contact because thermal stretching causes.In order to prevent the cooling-air in turbine case from going out from this gap to the side leakage of combustion gas stream, between tail pipe and guard shield, be provided with sealing component.
As such sealing component, such as, Patent Document 1 discloses Stern tube seal part.This Stern tube seal part is configured between the inner side guard shield of tail pipe and stator blade.Stern tube seal part, by the groove chimeric with the flange of tailpipe exit, the groove chimeric with the flange end of inner side guard shield, seals between tail pipe and inner side guard shield.
Patent documentation 1: Japanese Unexamined Patent Publication 2000-257862 publication
But, in such sealing component, there is following situation, that is, form recess in the region chimeric with guard shield, in this recess, brush seal is installed.Thus, the sealing between groove and the flange end of guard shield is made to improve.
But in order to be installed on the sealing member by brush seal, the region chimeric with sealing component of guard shield can reduce, thus when guard shield has stretched because of the impact of heat, there is the possibility that sealing component comes off from guard shield.
Model utility content
[problem that model utility will solve]
Even if the utility model provide a kind of also can suppress to come off from guard shield when guard shield has stretched because of the impact of heat sealing component and gas turbine.
[for solving the hand level of problem]
In order to solve above-mentioned problem, the utility model proposes following scheme.
Between sealing component in first method of the present utility model is configured in the burner of gas turbine tail pipe in the mode extended in the circumference of rotor shaft and the guard shield of stator blade, block the gap axially of the rotor shaft between described tail pipe and described guard shield, described sealing component possesses: the first engagement portion, it is arranged on described axial upstream side, and be connected with the end in the described axial downstream side of described tail pipe, and extend in the circumference of described rotor shaft, second engagement portion, it is arranged on described axial downstream side, and with chimeric with the protuberance towards described axial upstream side be formed on described guard shield in described axially overlapping mode, and extend in the circumferential direction, described second engagement portion has opposed faces opposed with described protuberance in the radial direction of described rotor shaft, the recess caved in the radial direction of described rotor shaft is formed in the end in the described axial downstream side of described opposed faces, the elastomer seal in the gap between this recess of blocking and opposed described protuberance is installed in described recess, described recess is formed in the mode that local extends in the circumferential.
According to such structure, by being formed locally the opposed faces of recess being provided with and installing for elastomer seal in the circumferential, can guaranteeing to arrange the region of elastomer seal and increasing the region chimeric with protuberance overlap.Therefore, it is possible to guarantee the sealing based on elastomer seal and the chimeric amount increased relative to protuberance.
In sealing component in second method of the present utility model, following mode can be taked, that is, in the first way, two end part and the central part of described circumference is formed in the circumferential in the mode be separated from each other with the described opposed faces of described recess spread configuration.
According to such structure, be formed at two end part and the central part of circumference in the circumferential with the opposed faces of recess spread configuration, recess can be formed in the mode clipped by opposed faces thus.Therefore, such as, the such elastomer seal of brush seal longer in the circumferential can be set.
In sealing component in Third Way of the present utility model, following mode can be taked, that is, in a second manner, be formed with the length of more than 10mm below 40mm in the circumferential direction with the described opposed faces of described recess spread configuration in the circumferential.
According to such structure, such as, the sealing component be formed with in order to ensure the MIN opposed faces needed for the chimeric amount relative to protuberance can be set for the guard shield of general size.
In sealing component in fourth way of the present utility model, following mode can be taked, that is, in a second manner or based on Third Way, be formed by built-up welding with the described opposed faces of described recess spread configuration in the circumferential.
According to such structure, formed after recess at the complete cycle throughout sealing surface, by means of only to for increase and the part of chimeric amount of protuberance to be welded in the mode of landfill recess and just can be formed opposed faces.
In sealing component in the 5th mode of the present utility model, following mode can be taked, that is, in the first way or based on second method, described elastomer seal is brush seal.
Gas turbine in 6th mode of the present utility model, possesses: first method is to any one sealing component of the 5th mode; There is the burner of described tail pipe; There is the stator blade of described guard shield.
According to such structure, when guard shield is flexible because of the impact of heat, sealing component can be suppressed to come off from guard shield.Therefore, it is possible to stably guarantee the sealing between burner and the guard shield of stator blade.
[model utility effect]
According to the utility model, increase chimeric amount relative to protuberance partly, even if sealing component also can be suppressed thus to come off from guard shield when guard shield is flexible because of the impact of heat by utilizing opposed faces.
Accompanying drawing explanation
Fig. 1 is the side view be described the major component notch flank of the gas turbine in mode of execution of the present utility model.
Fig. 2 is the major component sectional view of the gas turbine in mode of execution of the present utility model.
Fig. 3 is the major component sectional view around the stator blade in mode of execution of the present utility model.
Fig. 4 is the figure be described the sealing component in mode of execution of the present utility model.
Fig. 5 A is the sectional view that the state of sealing component at recess area place when observing the X-X section in Fig. 4 is described.
Fig. 5 B is the sectional view that the state of sealing component at recess area place when observing the Y-Y section in Fig. 4 is described.
Description of reference numerals
1 gas turbine
A pressurized air
G combustion gas
Da axially
Dc circumference
Dr is radial
10 compressors
20 burners
Ac axis
21 tail pipes
210 main bodys
211 lip parts
211a radial flange
22 fuel feeders
22a inner core
30 turbines
31 shells
Ar rotor shaft
33 turbine rotors
34 rotor subjects
35 moving vane row
36 moving vanes
37 moving vane main bodys
38 platforms
39 blades are followed
40 stator blade row
41 stator blades
42 stator blade main bodys
43 outboard shroud
Guard shield inside 45
451 boot main body
451a gas is through face
451b first side
451d inner peripheral surface
452 protuberances
40a first stator blade arranges
41a first stator blade
46 sealing plates
50 blade rings
52 heat insulation loop
60 segmentation rings
Pg combustion gas stream
7 sealing components
8 first engagement portions
81 first main parts
81a first main surface
82 first opposed portion
82a first surface
83 second opposed portion
83a second
9 second engagement portions
91 second main parts
91a second main surface
92 the 3rd opposed portion
92a the 3rd
93 the 4th opposed portion
93a fourth face
94b recess
α recess area
The non-recess area of β
95 brush seals
951 brush seal main parts
952 brush portions
Embodiment
Below, referring to figs. 1 through Fig. 5 B, mode of execution of the present utility model is described.
As shown in Figure 1, gas turbine 1 possesses: compression outside air and generate pressurized air A compressor 10, make fuel mix in pressurized air A and the multiple burners 20 making it burn and generate combustion gas G, the turbine 30 that driven by combustion gas G.
The turbine rotor 33 that turbine 30 possesses shell 31, rotates centered by rotor shaft Ar in this shell 31.This turbine rotor 33 is connected with the generator (not shown) such as generated electricity by the rotation of this turbine rotor 33.
Compressor 10 is configured in the side of rotor shaft Ar relative to turbine 30.The shell 31 of turbine 30 centered by rotor shaft Ar cylindrically.In compressor 10, using a part of pressurized air A as cooling-air to turbine 30, burner 20 supplies.The space in shell 31 is temporarily accumulated in by the pressurized air A after compressor 10 pressurizes.Multiple burner 20 is to be installed on this shell 31 in the mode at the spaced interval of circumferential Dc relative to rotor shaft Ar.
Herein, the direction that rotor shaft Ar extends is set to axial Da.Further, on axial Da, by the side being configured with turbine 30 being set to relative to burner 20 downstream side (on the right side of Fig. 1 paper) of axial Da, its opposition side is set to the upstream side (on the left of Fig. 1 paper) of axial Da.
By the circumferential Dc using rotor shaft Ar as benchmark referred to as circumferential Dc, by using this rotor shaft Ar as the radial Dr of benchmark referred to as radial Dr.
On radial Dr, the side away from rotor shaft Ar is set to outside radial Dr, namely its opposition side is set to inside radial Dr near the side of rotor shaft Ar.
Turbine rotor 33 has the rotor subject 34 that extends on axial Da using rotor shaft Ar as center and Da arrangement vertically and is installed on multiple moving vane row 35 of rotor subject 34.
As shown in Figure 2, each moving vane row 35 all relative to rotor shaft Ar circumferentially Dc be arranged with multiple moving vane 36 thus form circular using rotor shaft Ar as center.Moving vane 36 has the platform 38 inside the moving vane main body 37 extended on radial Dr, the radial Dr being arranged on this moving vane main body 37 and is arranged on the blade root 39 inside the radial Dr of this platform 38.Moving vane 36 is by imbedding rotor subject 34 by this blade root 39 and being fixed on rotor subject 34.
Stator blade row 40 are configured with at each upstream side of multiple moving vane row 35.Each stator blade row 40 all arrange adjacently and multiplely arrange stator blade 41 on circumferential Dc, thus it is circular to be configured to centered by rotor shaft Ar.Each stator blade 41 all has: the stator blade main body 42 extended outside radial Dr, be arranged on stator blade main body 42 radial Dr outside outboard shroud 43, be arranged on stator blade main body 42 radial Dr inside inner side guard shield 45.
Outside the radial Dr of moving vane row 35 and stator blade row 40 and inside the radial Dr of shell 31, there is cylindric blade ring 50 using rotor shaft Ar as center configuration.This blade ring 50 is fixed on shell 31.The outboard shroud 43 of stator blade 41 is linked by disconnected hot ring 52 with blade ring 50.
The outboard shroud 43 of stator blade row 40 adjacent on axial Da each other, is configured with multiple segmentation rings 60 of the circumferentially Dc arrangement using rotor shaft Ar as center.Circumferentially multiple segmentation rings 60 of Dc arrangement are formed as ring-type, inside its radial Dr, be configured with moving vane row 35.Circumferentially multiple segmentation rings 60 of Dc arrangement are all linked with blade ring 50 by disconnected hot ring 52.
The combustion gas stream Pg for combustion gas G flowing is formed in the shell 31 of turbine 30.Combustion gas stream Pg is by forming the inner side guard shield 45 of multiple stator blades 41 of stator blade row 40 and outboard shroud 43 and forming the platform 38 of multiple moving vanes 36 of moving vane row 35 in its downstream side and the segmentation ring 60 opposed with it is divided into ring-type around rotor subject 34.
As shown in Figure 3, on the inner side guard shield 45 and outboard shroud 43 of stator blade 41, possess and have with the aspectant gas of combustion gas stream Pg through the boot main body 451 of face 451a, from boot main body 451 to the protuberance 452 that the upstream side of axial Da extends.
Boot main body 451 is formed: towards the outer circumferential face in the outside of the radial Dr of inner side guard shield 45 and gas through face 451a, to extend inside radial Dr and towards the first side (side) 451b of axial Da from gas through face 451a.
Protuberance 452 extends from the first side 451b of the upstream side towards axial Da of boot main body 451 to the upstream side of axial Da.The protuberance 452 of present embodiment is formed at the position be separated inside radial Dr through face 451a from gas.The face of the inner side towards radial Dr of protuberance 452 be formed as with boot main body 451 be in same plane towards the face inside radial Dr.That is, the inner side towards radial Dr of protuberance 452 face and boot main body 451 towards the inner peripheral surface 451d forming inner side guard shield 45 together with the face inside radial Dr.Therefore, the thickness on the radial Dr of the Thickness Ratio boot main body 451 on the radial Dr of protuberance 452 is thin.Protuberance 452 is formed as section using rotor shaft Ar as the arc-shaped at center.
In stator blade row 40, be configured in and lean on the first stator blade 41a of the formation first stator blade row 40a of axial Da upstream side to be connected via the tail pipe 21 of sealing component 7 with following burner 20 most.
As shown in Figure 2, burner 20 possesses: the tail pipe 21 transported to turbine 30 by the combustion gas G of High Temperature High Pressure, in this tail pipe 21, supply the fuel feeder 22 of fuel and pressurized air A.
Fuel feeder 22 has and forms flame in inside and inner core 22a in tubular centered by axis Ac.
Tail pipe 21 is connected with inner core 22a, and is supplied to turbine 30 by the combustion gas G of the High Temperature High Pressure generated in inner core 22a.Tail pipe 21 is in tubular.Specifically, the exit opening in the downstream side on the axial Da of tail pipe 21 is roughly in square shape.Tail pipe 21 has: the cylinder main body 210 of the tubular extended along axis Ac, in the downstream side of axial Da from the lip part 211 that the outer circumferential face of cylinder main body 210 is outstanding.
It should be noted that, the axis Ac of the cylinder main body 210 in present embodiment refers to the line by position of centre of gravity in each section intersected in the direction extended with cylinder main body 210.
Cylinder main body 210 has combustion gas G at internal circulation.Cylinder main body 210 is formed as diminishing gradually from the upstream side of axial Da towards downstream side sectional area.
Lip part 211 is to cover the mode of the surrounding of the exit opening of cylinder main body 210 roughly in cubic ring-type.Protruding outside from the outer circumferential face of cylinder main body 210 towards combustion gas stream Pg of lip part 211.Lip part 211 forms the end in the downstream side of the axial Da of tail pipe 21.Lip part 211 has a pair radial flange portions 211a extended on radial Dr, a pair peripheral flange portion (not shown) extended on circumferential Dc.
As shown in Figure 3, radial flange portions 211a respectively from the outer circumferential face of cylinder main body 210 towards radial Dr outer circumferential face outstanding to detaching direction in the outer part compared with combustion gas stream Pg.As shown in Figure 2, a pair radial flange portions 211a is mutually opposing on radial Dr across exit opening.
Sealing component 7 is at burner 20 and the downstream side of axial Da being configured in burner 20 and and the Stern tube seal part circumferentially configured between the aspectant first stator blade row 40a of combustion gas stream Pg.Sealing component 7 closes the gap of the axis between the inner side guard shield 45 of the radial flange portions 211a of the tail pipe 21 of the burner 20 of gas turbine 1 and the first stator blade 41a of the first stator blade row 40a and outboard shroud 43.
In the present embodiment, sealing component 7 is divided into inner seal component 7a and outer side seal component 7b.The radial flange portions 211a configuration of inner seal component 7a and outer side seal component 7b respectively inside the radial Dr in the lip part 211 of roughly cubic ring-type or outside radial Dr.Inner seal component 7a is sticked in the radial flange portions 211a inside radial Dr and is sticked in the inner side guard shield 45 of the first stator blade 41a.In addition, outer side seal component 7b is sticked in the radial flange portions 211a outside radial Dr and is sticked in the outboard shroud 43 of the first stator blade 41a.
It should be noted that, the inner seal component 7a inside radial Dr and the outer side seal component 7b outside radial Dr with the axis Ac of tail pipe 21 for benchmark and substantially symmetrical shape.Therefore, below, mainly with the sealing component 7 (inner seal component 7a) being sticked in the inner side guard shield 45 inside radial Dr for typical example is described, but also can be equally applicable to outer side seal component 7b.Below, the title in explanation herein, reference character are labeled as " sealing component 7 " and are described.
Sealing component 7 extends on circumferential Dc.As shown in Figure 4, sealing component 7, when observing from axial Da, is the arc-shaped protruded outside radial Dr according to the mode being configured to ring-type centered by rotor shaft Ar.As shown in Figure 3, sealing component 7 possesses: the first engagement portion 8 being connected to the tail pipe 21 of burner 20 at the upstream side of axial Da, the second engagement portion 9 of inner side guard shield 45 being connected to the first stator blade 41a in the downstream side of axial Da.
First engagement portion 8 seals from the mode of leaking to combustion gas stream Pg side between lip part 211 and sealing component 7 not make the pressurized air A in shell 31.First engagement portion 8 is arranged on the upstream side on axial Da, is connected, and extends on circumferential Dc with the end in the downstream side on the axial Da of tail pipe 21.First engagement portion 8 of present embodiment has: the first main part 81 being formed with the first main surface 81a opposed with the face towards radial Dr of radial flange portions 211a, the first opposed portion 82 being formed with the first surface 82a opposed with the face of the upstream side towards axial Da of radial flange portions 211a, be formed with second opposed portion 83 of second 83a opposed with the face in the downstream side towards axial Da of radial flange portions 211a.
First main part 81 is formed as comprising axis Ac and the roughly rectangular shape longer on axial Da in the cross section of extending on radial Dr.First main part 81 is formed in compared with radial flange portions 211a by the position inside radial Dr.
First opposed portion 82 is given prominence to from the end of the upstream side of the axial Da of the first main part 81 towards the outer circumferential face of cylinder main body 210.First opposed portion 82 is formed as comprising axis Ac and the roughly rectangular shape longer on radial Dr in the cross section of extending on radial Dr.First opposed portion 82 is outstanding inside radial Dr from the first main part 81 by the position of the upstream side of axial Da compared with radial flange portions 211a.
Second opposed portion 83 is given prominence to from the end in the downstream side of the axial Da of the first main part 81 towards cylinder main body 210.Second opposed portion 83 is formed as comprising axis Ac and the roughly rectangular shape longer on radial Dr in the cross section of extending on radial Dr.Second opposed portion 83 is outstanding inside radial Dr from the first main part 81 by the position in the downstream side of axial Da compared with radial flange portions 211a.
First engagement portion 8 of present embodiment forms groove portion by second 83a towards the first main surface 81a outside radial Dr, the first surface 82a towards the downstream side of axial Da, the upstream side towards axial Da.By making radial flange portions 211a embed this groove portion from radial Dr, thus the first engagement portion 8 is engaged with radial flange portions 211a.
Second engagement portion 9 seals from the mode of leaking to combustion gas stream Pg side between protuberance 452 and sealing component 7 not make the pressurized air A in shell 31.Second engagement portion 9 is arranged on the downstream side on axial Da, chimeric with protuberance 452 in mode overlapping on axial Da, and extends on circumferential Dc.Second engagement portion 9 of present embodiment has: be formed with second main part 91 of the second main surface 91a opposed with the face of the upstream side towards axial Da of protuberance 452, be formed with the 3rd opposed portion 92 of three 92a opposed towards the face outside radial Dr of protuberance 452, be formed with the 4th opposed portion 93 with fourth face (opposed faces) 93a opposed towards the face inside radial Dr of protuberance 452.Second engagement portion 9 is provided with the brush seal 95 as elastomer seal.
Second main part 91 is outstanding from the end outside the radial Dr of the second opposed portion 83 towards the downstream side of axial Da.With regard to the second main part 91 of present embodiment, comprise axis Ac and the cross section of extending on radial Dr expands on radial Dr along with the downstream side towards axial Da.Second main part 91 is formed in gas through the aspectant position of face 451a.
3rd opposed portion 92 is given prominence to from the downstream side of the axial Da in the radial Dr lateral of the second main part 91.3rd opposed portion 92 is formed as comprising axis Ac and the roughly rectangular shape longer on axial Da in the cross section of extending on radial Dr.3rd opposed portion 92 compared with protuberance 452 by giving prominence to from the second main part 91 through the aspectant position of face 451b with gas outside radial Dr.
4th opposed portion 93 is given prominence to from the downstream side of the axial Da of side direction in the radial Dr of the second main part 91.4th opposed portion 93 is formed as comprising axis Ac and the roughly rectangular shape longer on axial Da in the cross section of extending on radial Dr.4th opposed portion 93 is being given prominence to from the second main part 91 by the position inside radial Dr compared with protuberance 452.
The fourth face 93a of the 4th opposed portion 93 is, opposed and when the second engagement portion 9 is chimeric with protuberance 452 and the sealing surface of protuberance 452 sliding contact towards the face inside radial Dr with protuberance 452.As shown in Figure 4, the end in the downstream side of fourth face 93a on axial Da is formed with the recess 94b caved on radial Dr, and this recess 94b is provided with the elastomer seal towards the gap between the face inside radial Dr blocked with opposed protuberance 452.Recess 94b is formed in the mode that part extends in the circumferential.Therefore, fourth face 93a has: be formed with the recess area α of recess 94b, adjoin and be not formed with the non-recess area β of recess 94b with recess area α on circumferential Dc.
Recess area α is formed at a part of circumferential Dc.In recess area α, as shown in Figure 5A, the recess 94b as depression installed for brush seal 95 is formed.Recess 94b is formed in the end of fourth face 93a, and the end face of this fourth face 93a is to the face in the downstream side towards axial Da of the 4th opposed portion 93.
Non-recess area β is, arranges and be not formed with the fourth face 93a of recess 94b in the mode arranged with recess 94b on circumferential Dc.The two end part of non-recess area β on circumferential Dc and central part are formed in the mode be separated from each other.In non-recess area β, as shown in Figure 5 B, recess 94b is not formed.Therefore, only recess 94b is not formed with at the two end part of circumferential Dc and central part.Be preferably, non-recess area β is formed with the length of more than 10mm below 40mm respectively on circumferential Dc.The non-recess area β of present embodiment, after the whole region of the circumferential Dc throughout fourth face 93a forms recess 94b, is formed by built-up welding.
As shown in Figure 3, seal between brush seal 95 pairs of protuberances 452 and fourth face 93a.As shown in Figure 5A, brush seal 95 has: be arranged on the brush seal main part 951 in recess 94b, from brush seal main part 951 towards radial Dr brush portion 952 protruding outside.
Brush seal main part 951 is rectangular-shaped and extend on circumferential Dc in section.
Brush portion 952 giving prominence to towards the face outside radial Dr from brush seal main part 951.Brush portion 952 forms brush by wire-like members is tied up bunchy.The brush portion 952 of present embodiment, along the bearing of trend of brush seal main part 951, circumferential Dc forms row.As shown in Figure 4, brush portion 952 tilts outstanding towards a side of circumferential Dc with the angle of 45 ° relative to radial Dr.
As shown in Figure 3, the second engagement portion 9 of present embodiment is by the 3rd 92a of the second main surface 91a towards the downstream side of axial Da, the inner side towards radial Dr, form groove portion towards the fourth face 93a outside radial Dr.By making protuberance 452 embed this groove portion from the downstream side of axial Da towards upstream side, thus the second engagement portion 9 engages with protuberance 452.
By the first engagement portion 8 and the second engagement portion 9, make sealing component 7 be sticked in the radial flange portions 211a of tail pipe 21 and the protuberance 452 of inner side guard shield 45, thus maintain the sealing between tail pipe 21 and inner side guard shield 45.
According to sealing component 7 as described above, with the fourth face 93a of protuberance 452 sliding contact on be formed with recess area α and non-recess area β, this recess area α is formed with the recess 94b installed for brush seal 95, and this non-recess area β is not formed with recess 94b.Therefore, it is possible to guarantee the region arranging brush seal 95 in recess area α, and in non-recess area β, increase the area with the fourth face 93a of protuberance 452 sliding contact.Therefore, it is possible to guarantee based on brush seal 95 with the sealing of protuberance 452, and the chimeric amount relative to protuberance 452 can be increased partly at the part place of circumferential Dc.Thus, even if when inner side guard shield 45 has stretched because of the impact of heat, sealing component also can be suppressed to come off from inner side guard shield 45.
Be formed with non-recess area β separated from each other at the two end part of circumferential Dc and central part, recess area α can be formed in the mode clipped by non-recess area β thus.Such as, therefore, it is possible to, brush seal 95 longer on circumferential Dc can be configured in recess 94b longlyer on circumferential Dc continuously and form recess area α.Thus, a small amount of brush seal 95 is only set, just can guarantees the sealing relative to protuberance 452, and the chimeric amount relative to protuberance 452 can be increased.
Non-recess area β is formed with the length of more than 10mm below 40mm on circumferential Dc, thus, such as, for the inner side guard shield 45 of general size, the sealing component 7 formed in order to ensure the MIN non-recess area needed for the chimeric amount relative to protuberance 452 can be set.
For non-recess area β, after forming recess 94b throughout the complete cycle of fourth face 93a, by for increase and the part of chimeric amount of protuberance 452 to be welded in the mode of landfill recess 94b and just can be formed non-recess area β.
By sealing component 7 is as described above used for gas turbine 1, when inner side guard shield 45 has stretched because of the impact of heat, sealing component 7 can be suppressed to come off from inner side guard shield 45.Therefore, it is possible to stably guarantee the sealing between burner 20 and inner side guard shield 45.
Above, mode of execution of the present utility model has been described in detail with reference to accompanying drawing, but each structure of each mode of execution and their combination etc. are only examples, in the scope not departing from purport of the present utility model, can carry out structure additional, omit, to replace and other change.In addition, the utility model is not implemented mode and limits, and is only defined by the claims.
It should be noted that, the utility model is not limited to the structure of the such sealing component of above-mentioned mode of execution 7, as long as be formed with the second engagement portion 9 of the first engagement portion 8 being connected to burner 20, the protuberance 452 being connected to stator blade 41.
Industrial applicibility
According to above-mentioned sealing component 7, by increasing the chimeric amount relative to protuberance 452 partly at non-recess area β, thus, even if sealing component also can be suppressed to come off from guard shield when guard shield is flexible because of the impact of heat.
Claims (6)
1. a sealing component, between its tail pipe being configured in the burner of gas turbine in the mode extended in the circumference of rotor shaft and the guard shield of stator blade, block the gap axially of the rotor shaft between described tail pipe and described guard shield, the feature of described sealing component is to possess:
First engagement portion, it is arranged on described axial upstream side, and is connected with the end in the described axial downstream side of described tail pipe, and extends in the circumference of described rotor shaft;
Second engagement portion, it is arranged on described axial downstream side, and with chimeric with the protuberance towards described axial upstream side be formed on described guard shield in described axially overlapping mode, and extend in the circumferential direction,
Described second engagement portion has opposed faces opposed with described protuberance in the radial direction of described rotor shaft, the recess caved in the radial direction of described rotor shaft is formed in the end in the described axial downstream side of described opposed faces, be provided with the elastomer seal in the gap between this recess of blocking and opposed described protuberance in described recess, described recess is formed in the mode that local extends in the circumferential.
2. sealing component according to claim 1, is characterized in that,
Be formed at two end part and the central part of described circumference in the circumferential in the mode be separated from each other with the described opposed faces of described recess spread configuration.
3. sealing component according to claim 1, is characterized in that,
Formed with the length of more than 10mm below 40mm in the circumferential direction with the described opposed faces of described recess spread configuration in the circumferential.
4. the sealing component according to Claims 2 or 3, is characterized in that,
Formed by built-up welding with the described opposed faces of described recess spread configuration in the circumferential.
5. sealing component according to claim 1 and 2, is characterized in that,
Described elastomer seal is brush seal.
6. a gas turbine, is characterized in that, possesses:
Described sealing component according to any one of claim 1 to 5;
There is the burner of described tail pipe;
There is the stator blade of described guard shield.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520176997.6U CN204627758U (en) | 2015-03-26 | 2015-03-26 | Sealing component and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520176997.6U CN204627758U (en) | 2015-03-26 | 2015-03-26 | Sealing component and gas turbine |
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| CN204627758U true CN204627758U (en) | 2015-09-09 |
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| CN201520176997.6U Active CN204627758U (en) | 2015-03-26 | 2015-03-26 | Sealing component and gas turbine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106121739A (en) * | 2016-08-11 | 2016-11-16 | 广东惠州天然气发电有限公司 | A kind of tail pipe sealing member |
| CN110410159A (en) * | 2018-04-27 | 2019-11-05 | 三菱重工业株式会社 | Gas turbine |
| CN114599859A (en) * | 2019-10-18 | 2022-06-07 | 西门子能源全球有限两合公司 | Rotor with a rotor component arranged between two rotor disks |
-
2015
- 2015-03-26 CN CN201520176997.6U patent/CN204627758U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106121739A (en) * | 2016-08-11 | 2016-11-16 | 广东惠州天然气发电有限公司 | A kind of tail pipe sealing member |
| CN110410159A (en) * | 2018-04-27 | 2019-11-05 | 三菱重工业株式会社 | Gas turbine |
| CN114599859A (en) * | 2019-10-18 | 2022-06-07 | 西门子能源全球有限两合公司 | Rotor with a rotor component arranged between two rotor disks |
| CN114599859B (en) * | 2019-10-18 | 2023-11-17 | 西门子能源全球有限两合公司 | Rotor with rotor components arranged between two rotor disks |
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