CN204552837U - The stator blade of gas turbine, stator blade inserting member and gas turbine - Google Patents
The stator blade of gas turbine, stator blade inserting member and gas turbine Download PDFInfo
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- CN204552837U CN204552837U CN201520175143.6U CN201520175143U CN204552837U CN 204552837 U CN204552837 U CN 204552837U CN 201520175143 U CN201520175143 U CN 201520175143U CN 204552837 U CN204552837 U CN 204552837U
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Abstract
The utility model provides a kind of stator blade, stator blade inserting member and the gas turbine that possess the gas turbine of enough maintainabilities and cooling performance.The stator blade of this gas turbine configures in the mode of intersecting with the flow direction of the working fluid moved along the axis of gas turbine from upstream side to downstream effluent, and possesses: the stator blade main body of the tubular that the radial direction along axis extends; Radial direction in the inner side of stator blade main body along axis extends, and between the inner peripheral surface of stator blade main body, form cooling-air stream, and is formed with multiple Cooling Holes in side, and is provided with the inserting member main body of the tubular of opening at radial outside and radially inner side; Be arranged on the inner side of inserting member main body and extend with tabular along the direction that inserting member main body extends, thus by the demarcation strip of the space of the inner side of inserting member main body separation; Be arranged on the inserting member base plate of the end of the radially inner side of inserting member main body, the end of the radially inner side of demarcation strip is separated setting with inserting member base plate.
Description
Technical field
The utility model relates to a kind of turbine blade and gas turbine.
Background technique
The turbine blade used in the stator blade and moving vane of such as gas turbine is exposed in the working fluid of high temperature, and therefore turbine blade generally possesses cooling structure.As an example of such cooling structure, the inside that can be set forth in turbine blade forms the mode of the cooling-air stream extended along blade height direction.The compressed-air actuated part generated by compressor is circulated in this cooling-air stream as cooling fluid.
When forming above-mentioned cooling-air stream, in the turbine blade of reality, the insert member (inserting member) of tubular is set by portion in the inner thus cooling fluid is practical being formed at the technology circulated in the gap between this inserting member and inner peripheral surface of turbine blade.As the example of turbine blade possessing such inserting member, in patent documentation 1, describe gas turbine stator blade.
The gas turbine stator blade recorded in patent documentation 1 possesses the inserting member that insertion is respectively arranged in multiple hollow holes of blade interior.Multiple cooling-air ejiction opening is formed in the side of inserting member.Cooling-air is imported from the side in blade height direction to the inside of such inserting member.The major part importing the cooling-air of inserting member inside is sprayed from above-mentioned cooling-air ejiction opening towards the inner peripheral surface of gas turbine stator blade.
Patent documentation 1: Japanese Unexamined Patent Publication 11-002103 publication
But, comprise small rubbish in the known cooling-air importing inserting member inside as described above.There is such rubbish is deposited in inserting member inside possibility along with cooling-air stream.When accumulation has rubbish, this rubbish can hinder the flowing of the cooling-air in stream, thus causes reducing the cooling effect of gas turbine stator blade.Therefore, the technology of the accumulation reducing above-mentioned this rubbish is expected to be useful in.But, in the gas turbine stator blade described in above-mentioned patent documentation 1, be difficult to the removal etc. carrying out such rubbish, therefore there is the possibility that cooling effect is limited.
Model utility content
[problem that model utility will solve]
The utility model is consider that such situation completes, and its object is to provides a kind of turbine blade and the gas turbine that possess enough maintainabilities and cooling performance.
[for solving the means of problem]
In order to solve above-mentioned problem, the utility model adopts following mechanism.
The gas turbine stator blade of a mode of the present utility model is the stator blade of the described gas turbine configured in the mode of intersecting with the flow direction of the working fluid moved along the axis of gas turbine from upstream side to downstream effluent, the stator blade of described gas turbine possesses: the stator blade main body of tubular, and its radial direction along described axis extends; The inserting member main body of tubular, its radial direction in the inner side of described stator blade main body along described axis extends, and cooling-air stream is formed between the inner peripheral surface of described stator blade main body, and be formed with multiple Cooling Holes in side, and radial outside and radially inner side are provided with opening; Demarcation strip, it is arranged on the inner side of described inserting member main body, and extends along the direction that described inserting member main body extends with tabular, is separated in the space of the inner side of described inserting member main body thus; And inserting member base plate, it is arranged on the end of the radially inner side of described inserting member main body, and the end of the radially inner side of described demarcation strip is separated setting with described inserting member base plate.
According to such structure, the intensity of inserting member main body can be improved by demarcation strip.Further, the end of the radially inner side of demarcation strip is separated with inserting member base plate.Thus, the multiple spaces formed by demarcation strip all with the open communication of inserting member main body.Therefore, the rubbish flowing into the inside of inserting member main body can not be piled up, and discharges from the outward opening portion of inserting member main body.
In the stator blade of the gas turbine of a mode of the present utility model, also following mode can be taked, that is, described inserting member base plate at least partially along with the upstream side of the flow direction from working fluid tilts to radially inner side towards downstream side from radial outside.
According to such structure, due to the inclination at least partially of inserting member base plate, therefore, it is possible to make the flowing of the fluid of the internal circulation in inserting member main body smooth and easy.
In the stator blade of the gas turbine of a mode of the present utility model, also can take following mode, that is, described inserting member base plate be formed with the rubbish extraction hole running through described inserting member base plate.
According to such structure, the rubbish in inserting member main body easily can be discharged by rubbish extraction hole.
In the stator blade of the gas turbine of a mode of the present utility model, also can take following mode, that is, the described inserting member base plate being formed with described rubbish extraction hole tilts.
According to such structure, space can be formed at the outside of rubbish extraction hole (that is, the radially inner side of axis).Therefore, it is possible to the rubbish be deposited in inserting member main body is easily discharged via the outside of rubbish extraction hole to inserting member main body.
In the stator blade of the gas turbine of a mode of the present utility model, also can take following mode, that is, described rubbish extraction hole has the bore size larger than the described Cooling Holes be formed in described inserting member main body.
According to such structure, the rubbish in inserting member main body more easily can be discharged by rubbish extraction hole.Further, because the bore size of rubbish extraction hole is larger than the bore size of Cooling Holes, therefore, it is possible to the possibility that reduction rubbish is blocked after Cooling Holes flowing.
In the gas turbine blades of a mode of the present utility model, also following mode can be taked, that is, when the bore size of described rubbish extraction hole being set to D1, the bore size of described Cooling Holes being set to D2, the relation meeting formula described later (1) is configured to.
1.5≤D1/D2≤3.0…(1)
According to such structure, the rubbish in inserting member main body easily can be discharged by rubbish extraction hole.Further, because the bore size of rubbish extraction hole is larger than the bore size of Cooling Holes, therefore, it is possible to the possibility that reduction rubbish is blocked after Cooling Holes flowing.
In the stator blade of the gas turbine of a mode of the present utility model, also can take following mode, that is, the bore size of described rubbish extraction hole is more than 1mm below 3mm.
According to such structure, the rubbish in inserting member main body easily can be discharged by rubbish extraction hole.
The stator blade inserting member of other modes of the present utility model is the stator blade inserting member of the tubular of the inner side of the stator blade inserting gas turbine, described stator blade inserting member possesses: inserting member main body, it extends with tubular from the radial outside of the axis of described gas turbine to radially inner side and is formed, and radial outside and radially inner side are provided with opening, and be provided with the multiple Cooling Holes run through in side; Demarcation strip, it is arranged on the inner side of described inserting member main body, and extends along the direction that described inserting member main body extends with tabular, is separated in the space of the inner side of described inserting member main body thus; And inserting member base plate, it is arranged on the end of the radially inner side of described inserting member main body, and close a part for the described opening of the described radially inner side of described inserting member main body, the end of the radially inner side of described demarcation strip is separated setting with described inserting member base plate.
According to such structure, by making the end of the radially inner side of demarcation strip be separated with inserting member base plate, thus the multiple spaces formed by demarcation strip all with the open communication of inserting member main body.Therefore, the rubbish flowing into the inside of inserting member main body can not be piled up, and discharges from the outward opening portion of inserting member main body.
The gas turbine of another other modes of the present utility model possesses the stator blade of the gas turbine of above-mentioned either type and at least one party of stator blade inserting member.
According to such structure, can obtain having for gas turbine stator blade and enough cooling performances of stator blade inserting member and the gas turbine of maintainability.
[model utility effect]
According to the utility model, the turbine blade and gas turbine that possess enough maintainabilities and cooling performance can be provided.
Accompanying drawing explanation
Fig. 1 is the figure of the gas turbine representing mode of execution of the present utility model.
Fig. 2 is the figure of the gas turbine stator blade observing mode of execution of the present utility model from the radial direction of axis.
Fig. 3 is the figure of the gas turbine stator blade observing mode of execution of the present utility model from the circumference of axis.
Fig. 4 is the figure of the variation of the gas turbine stator blade representing mode of execution of the present utility model.
Fig. 5 is the stereogram of the stator blade inserting member of mode of execution of the present utility model.
Description of reference numerals
1 ... compressor, 2 ... burner, 3 ... turbine, 7 ... closure, 8 ... rubbish extraction hole 9 ... demarcation strip, 9A ... the end of the radial outside of demarcation strip, 9B ... the end of the radially inner side of demarcation strip, 10 ... compressor drum, 11 ... compressor rotating shaft, 12 ... compressor case, 13 ... compressor moving vane, 14 ... compressor stator blade, 15 ... compression stream, 20 ... burner body, 21 ... nozzle, 30 ... turbine rotor, 31 ... rotatable shaft, 32 ... turbine moving blade, 33 ... turbine stator vane, 34 ... turbine case, 35 ... turbine flow path, 50 ... cooling air intake, 51 ... cooling-air exports, 52 ... inserting member hollow portion, 53 ... front edge, 54 ... hinder marginal part, 55 ... pressure side 55A ... suction surface, 55B ... pressure surface, 56 ... hollow portion inner peripheral surface, 57 ... film-cooling hole 60 ... inserting member main body, 61 ... inserting member base plate, 62 ... inserting member outer circumferential face, 63 ... cooling-air stream, 64 ... inserting member inner peripheral surface, 65 ... inserting member Cooling Holes, 67 ... tap hole, 71 ... closure main body, 72 ... body flange, 73 ... closure penetration hole, 90 ... beam parts, 100 ... gas turbine 9X ... hollow portion is interval, A ... cooling-air, B1 ... blade body, B2 ... inserting member, B3 ... outboard shroud, B4 ... inner side guard shield, C ... pressurized air, F ... working fluid, G ... combustion gas H ... interconnecting part, O ... axis, S ... interval, TB ... turbine blade, V ... blade body hollow portion Vs ... little space
Embodiment
[mode of execution]
Below, be described with reference to the gas turbine 100 of Fig. 1 to mode of execution of the present utility model.As shown in Figure 1, gas turbine 100 possesses: compression extraneous gas and generate pressurized air C compressor 1, make the fuel that comes from the supply of fuel supply source and the pressurized air C turbine 3 that mixes combining combustion and generate the burner 2 of combustion gas G, driven by the combustion gas G of the High Temperature High Pressure generated by burner 2.
Compressor 1 possesses the compressor drum 10 rotated around axes O, the compressor case 12 surrounding this compressor drum 10 from outer circumferential side.The space formed between the outer circumferential face of compressor drum 10 and the inner peripheral surface of the compressor case 12 opposed with this outer circumferential face is formed as the compression stream 15 circulated for pressurized air C.
Compressor drum 10 has: along axes O extend and the compressor rotating shaft 11 that can rotate around this axes O, on the outer circumferential face of this compressor rotating shaft 11 along multiple compressor moving vanes 13 that the circumference of axes O and radial direction arrange respectively at spaced intervals.Further, on the inner peripheral surface of compressor case 12, multiple compressor stator blade 14 is arranged with respectively at spaced intervals along the circumference of axes O and radial direction.
Compressor moving vane 13 extends from the outer circumferential face of compressor drum 10 towards radial outside.On the other hand, compressor stator blade 14 roughly extends towards the radially inner side of axes O from the inner peripheral surface of compressor case 12.
Compressor stator blade 14 and compressor moving vane 13 are exposed in above-mentioned compression stream 15, and alternately arrange when observing from axes O direction.More specifically, from the side in axes O direction, be provided with the compressor stator blade 14 of the first order, the compressor moving vane 13 of the first order, the compressor stator blade 14 of the second level, the second level compressor moving vane 13 ...These compressor stator blades 14 and compressor moving vane 13 all have the section shape of leaf type when observing from radial direction.
The extraneous gas be imported in compressor 1 is compressed by circulating this compression stream 15 from the side in axes O direction towards opposite side becomes pressurized air C thus.
Burner 2 possesses: spray the nozzle 21 of the fuel from outside supply, be arranged on the burner body 20 of the tubular at the rear of the injection direction of this nozzle 21.In the inside of burner body 20, form combustion zone because of the mixture combustion of fuel and above-mentioned pressurized air C, and generate the combustion gas G as the working fluid F in turbine 3 described later.
Turbine 3 possesses and is connected in axes O with above-mentioned compressor drum 10 and the turbine rotor 30 rotated integratedly, the turbine case 34 of surrounding this turbine rotor 30 from outer circumferential side.The space formed between the outer circumferential face of turbine rotor 30 and the inner peripheral surface of the turbine case 34 opposed with this outer circumferential face is formed as the turbine flow path 35 circulated for working fluid F.
Turbine rotor 30 possesses: along axes O extend rotatable shaft 31, on the outer circumferential face of this rotatable shaft 31 along multiple turbine moving blades 32 that the circumference of axes O and radial direction arrange at spaced intervals.On the inner peripheral surface of turbine case 34, be arranged with multiple turbine stator vane 33 (gas turbine stator blade 33) at spaced intervals along the circumference of axes O and radial direction.
The compressor moving vane 13 of turbine moving blade 32 also with above-mentioned is identical, roughly extends towards the radial outside of axes O from the outer circumferential face of turbine rotor 30.On the other hand, turbine stator vane 33 roughly extends towards the radially inner side of axes O from the inner peripheral surface of turbine case 34.That is, these turbine moving blades 32 and turbine stator vane 33 all configure in the mode of intersecting with the flow direction of above-mentioned working fluid F.
Further, turbine stator vane 33 and turbine moving blade 32 are exposed in above-mentioned turbine flow path 35, and alternately arrange when observing from axes O direction.Specifically, from the side in axes O direction, be provided with the turbine stator vane 33 of the first order, the turbine moving blade 32 of the first order, the turbine stator vane 33 of the second level, the second level turbine moving blade 32 ...Further, these turbine stator vanes 33 and turbine moving blade 32 all have the section shape of leaf type when observing from radial direction.
The combustion gas G generated by above-mentioned burner 2 flows in above-mentioned turbine flow path 35 as working fluid F.Working fluid F circulates turbine flow path 35 from the side in axes O direction towards opposite side.It should be noted that, in the following description, the rear side of the flow direction of this working fluid F is called upstream side, being called downstream side by being positioned at the side contrary with this upstream side.
Working fluid F collides with above-mentioned turbine stator vane 33 and turbine moving blade 32 during circulation in turbine flow path 35.Thus, turbine rotor 30 is integrated with compressor drum 10 one-tenth and rotates around axes O.This rotary motion to the not shown external equipment transmission being connected to gas turbine 100, and for various uses.
Here, the combustion gas G circulated as working fluid F in turbine flow path 35 is the gas of the High Temperature High Pressure generated via the compression of compressor 1, the burning of burner 2.Therefore, above-mentioned turbine stator vane 33 and turbine moving blade 32, in the whole running of gas turbine 100, are exposed in the heat of this high temperature.When being exposed to normally in such heat, there is the possibility producing the distortion caused because of heat etc. in these turbine stator vanes 33 and turbine moving blade 32.
Therefore, in the present embodiment, especially following cooling structure is adopted in order to cooling turbine stator blade 33.This cooling structure carries out the cooling of turbine stator vane 33 by the part of the pressurized air C generated by above-mentioned compressor 1 is used as cooling-air A.
It should be noted that, as described above, turbine stator vane 33 is arranged in turbine case 34, and on the other hand, turbine moving blade 32 is arranged on turbine rotor 30.But, because the structure as blade body is all identical with effect, therefore in the present embodiment these turbine stator vanes 33 and turbine moving blade 32 are generically and collectively referred to as turbine blade TB, below with turbine stator vane 33 for representative is described.
As shown in Figure 2 and Figure 3, the turbine stator vane 33 of present embodiment possesses: the blade body B1 (stator blade main body B1) forming the profile of this turbine stator vane 33, the inserting member B2 (stator blade inserting member B2) inserting the inside of this blade body B1, be arranged on the outboard shroud B3 of the radial outside of blade body B1, be arranged on the inner side guard shield B4 of the end of opposition side and radially inner side.
Outboard shroud B3 configures in the mode opposed with the inner peripheral surface of turbine case 34.Turbine stator vane 33 is supported by the inner peripheral surface side of turbine case 34 by outboard shroud B3.Further, this outboard shroud B3 is provided with the cooling air intake 50 that the radial direction along axes O runs through.This cooling air intake 50 is communicated in inserting member hollow portion 52 described later, thus the pressurized air C generated by above-mentioned compressor 1 is directed into this inserting member hollow portion 52.
Inner side guard shield B4 configures in the mode opposed with the outer circumferential face of above-mentioned turbine rotor 30 from radial outside.Concrete structure although not shown, but, be preferably, inside this guard shield B4 axes O direction on face in the sealing configuration be provided with on the face of radially inner side for sealing the fluid between the outer circumferential face of turbine rotor 30.
Further, inner side guard shield B4 is formed with the cooling-air outlet 51 that the cooling-air A for the hollow portion by have passed blade body B1 as described above discharges towards radially inner side.That is, the cooling-air A flowed into by the cooling air intake 50 of outboard shroud B3, after the hollow portion passing through blade body B1, is discharged towards the outside from cooling-air outlet 51.
Blade body B1 is provided with between the outboard shroud B3 formed as described above and inner side guard shield B4.Blade body B1 is the component that section is formed as leaf type when observing from the radial direction of axes O.The side of the flow direction upstream side of the Workflow-oriented body F in this blade body B1 is set to front edge 53, the side of side is for the downstream set to hinder marginal part 54.
A pair pressure side 55 forming the side of blade body B1, along with from this front edge 53 towards hinder marginal part 54, gently bends to side.Face convexly in these pressure sides 55 is set to suction surface 55A, face is concavely set to pressure surface 55B.
Further, blade body B1 is tubular by being formed as hollow.The space of the inner side of blade body B1 is formed as blade body hollow portion V.More specifically, above-mentioned front edge 53, hinder marginal part 54 and a pair pressure side 55 that form the profile of blade body B1 are formed as all having the lamellar of roughly the same thickness size when observing from the radial direction of axes O.Thus, the hollow portion inner peripheral surface 56 as the inner peripheral surface of blade body B1 has the contour shape roughly the same with blade body B1 when observing from the radial direction of axes O.
Be formed as in laminal blade body B1, in a part for particularly pressure side 55 in the present embodiment, be formed with multiple perforates that through-thickness runs through this pressure side 55.These perforates are formed as film-cooling hole 57 respectively.Particular content describes below, and the cooling-air A importing the inside of blade body B1 is sprayed by the plurality of film-cooling hole 57, and circulates along each pressure side 55.
Inserting member B2 is the component of the tubular of the inside being configured in blade body hollow portion V.More specifically, as shown in Figure 5, this inserting member B2 has: the inserting member main body 60 of the tubular roughly extended along the radial direction of axes O, be arranged on the open-ended inserting member base plate 61 of the radially inner side of this inserting member main body 60.
As shown in Figure 2 and Figure 3, the inserting member main body 60 in present embodiment, when observing from the radial direction of axes O, in the shape corresponding with the profile line of the hollow portion inner peripheral surface 56 of blade body B1, and has the sectional area less than blade body hollow portion V.In other words, inserting member main body 60 is in the shape roughly similar to the shape of the hollow portion inner peripheral surface 56 of blade body B1.
Thus, between the inserting member outer circumferential face 62 and the hollow portion inner peripheral surface 56 of blade body B1 in the face in the outside of formation inserting member main body 60, gap is formed.Particular content describes below, and this gap is formed as the cooling-air stream 63 for cooling-air A circulation.Further, the space of the inner side of the inserting member main body 60 of tubular is formed as inserting member hollow portion 52.The face forming the face of this inserting member hollow portion 52 and the inner side of inserting member main body 60 is formed as inserting member inner peripheral surface 64.
Further, inserting member outer circumferential face 62 is formed with the multiple inserting member Cooling Holes 65 (Cooling Holes) be communicated with outside (that is, cooling-air stream 63) by this inserting member hollow portion 52.These inserting member Cooling Holes 65 radially roughly separate equal intervals and arrange on inserting member outer circumferential face 62.
The end of the radial outside in the radial two end part of inserting member main body 60 is supported by above-mentioned outboard shroud B3.On the other hand, the end of the radially inner side of inserting member main body 60 is supported by above-mentioned inner side guard shield B4.
The inserting member base plate 61 of this opening closed is provided with at the opening of the end of the radially inner side of inserting member main body 60.This inserting member base plate 61 is the component of the tabular roughly extended along axes O direction.More specifically, this inserting member base plate 61 along with the upstream side of the flow direction from above-mentioned working fluid F is towards downstream side, and tilts from radial outside to radially inner side.In other words, inserting member base plate 61 is constant angle when observing from the circumference of axes O relative to this axes O.
Further, because inserting member base plate 61 tilts as described above, between inserting member base plate 61 and inner side guard shield B4, the space of a part of blade body hollow portion V is therefore formed into.This space is formed as the little SPACE V s when observing from the direction orthogonal with the bearing of trend of turbine stator vane 33 roughly in chock type.Particular content describes below, and the rubbish of being discharged by above-mentioned rubbish extraction hole 8 flows into this little SPACE V s.
The radial direction be formed in the region in the downstream side of inserting member base plate 61 along axes O runs through opening and the tap hole 67 of this inserting member base plate 61.This tap hole 67 exports 51 with the cooling-air of above-mentioned inner side guard shield B4 and is communicated with.Further, inserting member base plate 61 is provided with the closure 7 of closed above-mentioned tap hole 67 and cooling-air outlet 51.
This closure 7 has: closure main body 71, and it has the roughly the same overall size of bore size exporting 51 with tap hole 67 and cooling-air, thus exports 51 mutually chimeric with these tap holes 67, cooling-air; Body flange 72, it supports this closure main body 71 from the radially inner side of axes O and abuts with inner side guard shield B4.The closure 7 be entrenched in tap hole 67 and cooling-air outlet 51 is abutted by the face of the radial outside of this body flange 72 with inner side guard shield B4 thus is fixedly supported upon fixed position.
Further, closure 7 is formed runs through above-mentioned closure main body 71 and the closure penetration hole 73 of body flange 72 in the mode of the radial direction throughout axes O.The bore size of closure penetration hole 73 and shape, position suitably can be determined according to design and specification.In the present embodiment, the region of the substantial middle during closure penetration hole 73 is arranged on the axes O direction of closure 7 extension size.
Be formed with the rubbish extraction hole 8 roughly running through inserting member base plate 61 along the radial direction of axes O in the region (that is, compared with above-mentioned tap hole 67 by the region of upstream side) of the upstream side of inserting member base plate 61 identically with tap hole 67.
Above-mentioned inserting member inner peripheral surface 64 is provided with the demarcation strip 9 that the radial direction along axes O extends.This demarcation strip 9 is the component of tabular inserting member hollow portion 52 being divided into multiple interval S.More specifically, inserting member hollow portion 52 is roughly separated thus is formed multiple interval S by this demarcation strip 9 on axes O direction.In the present embodiment, in inserting member hollow portion 52, a demarcation strip 9 is provided with.Thus, inserting member hollow portion 52 is split into two interval S.
Below this demarcation strip 9 is specifically described.As shown in Figure 3, demarcation strip 9 is the component of the roughly tabular radially extended in inserting member hollow portion 52.The end 9A of the radial outside of demarcation strip 9 is positioned at the position by radially inner side compared with the end of the radial outside of inserting member main body 60 and blade body B1.On the other hand, the end 9B of the radially inner side of demarcation strip 9 to be located at when observing from axes O direction compared with above-mentioned inserting member base plate 61 by the position of radial outside.In other words, demarcation strip 9 is arranged on the region comprising central authorities in the elongated area of the radial direction of inserting member hollow portion 52.
The end 9B of the radially inner side of this demarcation strip 9 is separated diametrically with inserting member base plate 61 thus forms gap.This gap is formed as the interconnecting part H communicated with each other by multiple interval S mutually adjacent in above-mentioned inserting member hollow portion 52.
Further, above-mentioned rubbish extraction hole 8 to be located at when observing from the radial direction of axes O compared with the end of the radially inner side of demarcation strip 9 by upstream side.That is, rubbish extraction hole 8 is towards the inside opening of the interval S of the upstream side in two the interval S formed by demarcation strip 9.
In the present embodiment, the bore size of this rubbish extraction hole 8 is set as larger than the bore size of the inserting member Cooling Holes 65 be formed on above-mentioned inserting member B2.Specifically, this rubbish extraction hole 8 is formed as satisfied following relation.When the bore size of rubbish extraction hole 8 being set to D1, the bore size of the inserting member Cooling Holes 65 be formed in above-mentioned inserting member main body 60 being set to D2, the relation of these D1 and D2 is specified by following formula (1).
1.5≤D1/D2≤3.0…(1)
On the basis considering the relation shown in above-mentioned formula (1), be preferably, the concrete opening size of rubbish extraction hole 8 be set as more than 0.5mm below 4mm, be more preferably, be set as more than 1mm below 3mm.Most preferably be, the bore size of rubbish extraction hole 8 is set as 2mm.
The turbine blade TB form as above picture and the action of gas turbine 100 are described.
First, when starting gas turbine 100, compressor 1 is driven.Specifically, by not shown starting arrangement, above-mentioned compressor drum 10 and turbine rotor 30 is made to start to rotate around axes O.During this period, along with the rotation of compressor drum 10, the compressor moving vane 13 be exposed in compression stream 15 rotates, and the gas (air) of the outside of compressor 1 flows in compression stream 15 thus.This air is along with circulating along axes O in compression stream 15 thus being compressed by compressor moving vane 13 and compressor stator blade 14 successively and become the pressurized air C of high pressure.
Then, this pressurized air C is supplied to burner 2.In the inside of burner 2, the mixed gas of the fuel that ejects from nozzle 21 as described above and pressurized air C burns and generates the combustion gas G of High Temperature High Pressure.
Then, the turbine 3 after combustion gas G inflow.In turbine 3, these combustion gas G circulates in above-mentioned turbine flow path 35 as working fluid F.Working fluid F circulates towards downstream side along axes O from upstream side in turbine flow path 35.Collided with the turbine moving blade 32 be exposed in turbine flow path 35 by working fluid F, the turbine rotor 30 supporting turbine moving blade 32 is rotated around axes O.It should be noted that, because compressor drum 10 and this turbine rotor 30 of compressor 1 link into an integrated entity, therefore along with the starting of above-mentioned compressor 1, turbine rotor 30 also becomes the state of rotation.More specifically, the working fluid F of High Temperature High Pressure collides with the turbine rotor 30 rotated in advance, turbine moving blade 32, thus the rotational speed of turbine rotor 30 (rotating speed) increases further.Accompany with it, the rotating speed of compressor drum 10 also increases, and therefore the pressure of pressurized air C also increases further.Below, by carrying out such circulation continuously and repeatedly, make compressor drum 10 and turbine rotor 30 High Rotation Speed.When reaching desired rotating speed, by the emitted dose etc. of the fuel of control combustion device 2, and maintain this rotating speed, thus gas turbine 100 becomes steady running state.
Here, the combustion gas G of High Temperature High Pressure flows into turbine flow path 35 as working fluid F as described above, therefore needs to implement cooling initiatively to the component contacted with these combustion gas G.Particularly, the turbine stator vane 33 to being directly exposed in turbine flow path 35 in these combustion gas G is needed to implement sufficient cooling.In the gas turbine 100 of reality, the part of the pressurized air C generated by compressor 1 supplies to turbine 3 via the stream, pipe arrangement etc. (not shown) suitably arranged.A part of this pressurized air C uses as cooling-air A.
In the turbine 3 of present embodiment, so a part of pressurized air C imports the inside of turbine stator vane 33 as cooling-air A.Specifically, as shown in Figure 3, cooling-air A flows into the inside (that is, inserting member hollow portion 52) of the inserting member main body 60 in turbine stator vane 33 by the cooling air intake 50 being arranged on the outboard shroud B3 on turbine stator vane 33.
The cooling-air A flowing into inserting member hollow portion 52 roughly circulates in this inserting member hollow portion 52 from the radial outside of axes O towards inner side.In inserting member hollow portion 52 during circulation, a part of cooling-air A blows out to the outside (that is, cooling-air stream 63) of inserting member main body 60 by being arranged on the inserting member Cooling Holes 65 in inserting member main body 60.By circulating in cooling-air stream 63, first the hollow portion inner peripheral surface 56 of blade body B1 is cooled.
The another part of the cooling-air A flowed along hollow portion inner peripheral surface 56 blows out to the pressure side 55 of blade body B1 by being arranged on the multiple film-cooling holes 57 on blade body B1.Thus, the pressure side 55 of blade body B1 is cooled.As mentioned above, the inner and outer of blade body B1 cools by the cooling-air A by being fed to the inside of blade body B1.
On the other hand, in above-mentioned cooling-air A do not flow into cooling-air stream 63 and the part stayed in inserting member hollow portion 52 arrives the closure 7 be entrenched on inserting member base plate 61, discharged by the radial inside of closure penetration hole 73 guard shield B4 to the inside.Particularly, in the present embodiment, because inserting member base plate 61 tilts, therefore inserting member hollow portion 52 is along with from the radial outside of axes O towards radially inner side (tap hole 67), and the area of section radially reduces gradually, and roughly in taper.Thus, in inserting member hollow portion 52, the flow velocity of the cooling-air A of circulation increases gradually along with close to tap hole 67.Therefore, it is possible to make the circulation of the cooling-air A in inserting member hollow portion 52 more smooth and easy.
It should be noted that, concrete structure although not shown, but can make as described above to the inside guard shield B4 side discharge cooling-air A again return in turbine flow path 35, thus as the leakage for reducing working fluid F etc. sealed department and use.
But being directed into as described above may containing rubbish such as small dust in the cooling-air A of the inside of turbine stator vane 33.The major part of such rubbish is discharged to the outside of inserting member B2 by above-mentioned tap hole 67 (closure penetration hole 73), inserting member Cooling Holes 65.Such as, the rubbish be discharged by tap hole 67 flows in the working fluid F of High Temperature High Pressure burned as described above.Further, the rubbish flowed into cooling-air stream 63 from inserting member Cooling Holes 65 is also discharged to the outside of blade body B1 by film-cooling hole 57, flows in working fluid F burned.
But, also can predict, the situation through Long-Time Service, in extraneous gas, comprise the environment harsh compared with multiparticle, dust etc. under use when, there is rubbish and be not fully discharged to the outside of inserting member B2 and the possibility of residual packing in inserting member hollow portion 52.
But, in the gas turbine 100 and turbine stator vane 33 of present embodiment, owing to being formed with rubbish extraction hole 8 on inserting member base plate 61, therefore, it is possible to the rubbish remained in inserting member hollow portion 52 is discharged to above-mentioned little SPACE V s.That is, even if through Long-Time Service, in the turbine stator vane 33 of present embodiment, the possibility of piling up rubbish in inserting member hollow portion 52 can be also reduced in.From rubbish extraction hole 8 be discharged to rubbish little SPACE V s via cooling-air stream 63 from film-cooling hole 57 to after the outside of blade body B1 is discharged, burnt by working fluid F.
Further, above-mentioned cooling-air stream 63 and little SPACE V s when the upkeep operation of gas turbine 100 etc. such as by taking off the operation that turbine stator vane 33 just can easily carry out from outside, therefore, it is possible to remove the rubbish of accumulation comparatively simply.That is, according to above-mentioned structure, the maintainability of turbine blade TB can be improved.
Like this, owing to inhibit the accumulation of the rubbish of the inside of turbine stator vane 33, therefore, it is possible to the possibility that the inserting member Cooling Holes 65 that fully reduction is above-mentioned, film-cooling hole 57 are blocked by rubbish.Thereby, it is possible to the cooling effect of long term maintenance turbine blade TB (turbine stator vane 33, turbine moving blade 32), thus the more stable utilization of gas turbine 100 can be realized.
Further, in above-mentioned turbine stator vane 33, rubbish extraction hole 8 has the bore size larger than the Cooling Holes be formed in inserting member main body 60.Specifically, when the bore size of rubbish extraction hole 8 being set to D1, the bore size of Cooling Holes being set to D2, be configured to the relation meeting above-mentioned formula (1).
According to such structure, the rubbish in inserting member main body 60 easily can be taken out by rubbish extraction hole 8.Further, because the bore size of rubbish extraction hole 8 is larger than the bore size of Cooling Holes, therefore, it is possible to the possibility reducing rubbish to flow towards Cooling Holes further and blocked.
Above, with reference to accompanying drawing, mode of execution of the present utility model is illustrated.But, only otherwise depart from purport of the present utility model, then can apply various change to above-mentioned mode of execution.
Such as, in the above-described embodiment, the example being provided with an inserting member B2 in the inside (blade body hollow portion V) of blade body B1 is illustrated.But the structure of blade body B1 and inserting member B2 is not limited to said structure.Specifically, as shown in Figure 4, also can be arranged on when observing blade body B1 from the radial direction of axes O on the bearing of trend of turbine blade TB the beam parts 90 that the hollow portion of blade body B1 is split.By these beam parts 90, blade body hollow portion V is divided into the interval 9X of hollow portion of multiple (three) from front edge 53 to hinder marginal part 54.In the example of this this figure external, adopt the structure that above-mentioned inserting member B2 is set respectively in the interval 9X of multiple hollow portion.
Thereby, it is possible to improve the intensity of blade body B1 further.And, compared with above-mentioned mode of execution, the respective volume of inserting member hollow portion 52 can be reduced.Thus, due to the pressure of the cooling-air A of the inside of each inserting member hollow portion 52 can be improved, therefore, it is possible to increase the flow velocity of the cooling-air A discharged in cooling flowing path.Therefore, it is possible to improve the cooling effect to turbine blade TB further.
Further, according to structure as above, owing to arranging inserting member B2 in the interval 9X of each hollow portion, therefore, it is possible to increase the number of the rubbish extraction hole 8 arranged in a turbine blade TB.Thus, even if when rubbish flows into the inside of turbine blade TB, also can fully and promptly be discharged.
Claims (12)
1. a stator blade for gas turbine, it configures in the mode of intersecting with the flow direction of the working fluid moved along the axis of gas turbine from upstream side to downstream effluent, and the feature of the stator blade of described gas turbine is to possess:
The stator blade main body of tubular, its radial direction along described axis extends;
The inserting member main body of tubular, its radial direction in the inner side of described stator blade main body along described axis extends, and cooling-air stream is formed between the inner peripheral surface of described stator blade main body, and be formed with multiple Cooling Holes in side, and radial outside and radially inner side are provided with opening;
Demarcation strip, it is arranged on the inner side of described inserting member main body, and extends along the direction that described inserting member main body extends with tabular, is separated in the space of the inner side of described inserting member main body thus; And
Inserting member base plate, it is arranged on the end of the radially inner side of described inserting member main body,
The end of the radially inner side of described demarcation strip is separated setting with described inserting member base plate.
2. the stator blade of gas turbine according to claim 1, is characterized in that,
Described inserting member base plate at least partially along with the upstream side of the flow direction from working fluid tilts to radially inner side towards downstream side from radial outside.
3. the stator blade of gas turbine according to claim 1 and 2, is characterized in that,
Described inserting member base plate is formed the rubbish extraction hole running through described inserting member base plate.
4. the stator blade of gas turbine according to claim 3, is characterized in that,
The described inserting member base plate being formed with described rubbish extraction hole tilts.
5. the stator blade of gas turbine according to claim 3, is characterized in that,
Described rubbish extraction hole has the bore size larger than the described Cooling Holes be formed in described inserting member main body.
6. the stator blade of gas turbine according to claim 4, is characterized in that,
Described rubbish extraction hole has the bore size larger than the described Cooling Holes be formed in described inserting member main body.
7. the stator blade of gas turbine according to claim 3, is characterized in that,
When the bore size of described rubbish extraction hole being set to D1, the bore size of described Cooling Holes being set to D2, meet following relation,
1.5≤D1/D2≤3.0。
8. the stator blade of gas turbine according to claim 4, is characterized in that,
When the bore size of described rubbish extraction hole being set to D1, the bore size of described Cooling Holes being set to D2, meet following relation,
1.5≤D1/D2≤3.0。
9. the stator blade of gas turbine according to claim 3, is characterized in that,
The bore size of described rubbish extraction hole is more than 1mm below 3mm.
10. the stator blade of gas turbine according to claim 4, is characterized in that,
The bore size of described rubbish extraction hole is more than 1mm below 3mm.
11. 1 kinds of stator blade inserting members, it is the stator blade inserting member of the tubular of the inner side of the stator blade being inserted into gas turbine, and the feature of described stator blade inserting member is to possess:
Inserting member main body, it extends with tubular from the radial outside of the axis of described gas turbine to radially inner side and is formed, and radial outside and radially inner side are provided with opening, and is provided with the multiple Cooling Holes run through in side;
Demarcation strip, it is arranged on the inner side of described inserting member main body, and extends along the direction that described inserting member main body extends with tabular, is separated in the space of the inner side of described inserting member main body thus; And
Inserting member base plate, it is arranged on the end of the radially inner side of described inserting member main body, closes a part for the described opening of the described radially inner side of described inserting member main body,
The end of the radially inner side of described demarcation strip is separated setting with described inserting member base plate.
12. 1 kinds of gas turbines, is characterized in that, possess at least one party in the stator blade of the gas turbine according to any one of claim 1 to 10 and stator blade inserting member according to claim 11.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520175143.6U CN204552837U (en) | 2015-03-26 | 2015-03-26 | The stator blade of gas turbine, stator blade inserting member and gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520175143.6U CN204552837U (en) | 2015-03-26 | 2015-03-26 | The stator blade of gas turbine, stator blade inserting member and gas turbine |
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| CN204552837U true CN204552837U (en) | 2015-08-12 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106499449A (en) * | 2015-09-08 | 2017-03-15 | 通用电气公司 | Article, component and the method for forming article |
| CN110529197A (en) * | 2019-10-10 | 2019-12-03 | 兰州长城机械工程有限公司 | A kind of variable stator vane angle device suitable for high-temperature flue gas turbine |
| CN114382554A (en) * | 2020-10-06 | 2022-04-22 | 三菱动力株式会社 | Gas turbine stationary blade |
-
2015
- 2015-03-26 CN CN201520175143.6U patent/CN204552837U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106499449A (en) * | 2015-09-08 | 2017-03-15 | 通用电气公司 | Article, component and the method for forming article |
| JP2017053351A (en) * | 2015-09-08 | 2017-03-16 | ゼネラル・エレクトリック・カンパニイ | Article, component, and method of forming article |
| CN110529197A (en) * | 2019-10-10 | 2019-12-03 | 兰州长城机械工程有限公司 | A kind of variable stator vane angle device suitable for high-temperature flue gas turbine |
| CN114382554A (en) * | 2020-10-06 | 2022-04-22 | 三菱动力株式会社 | Gas turbine stationary blade |
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